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 ^^»y:..:^.vxJ..:^y~"'- - ' "- ^ ■■y RM E54E25 
 
 RESEARCH MEMORANDUM 
 
 COOLING CHARACTERISTICS OF A TRANSPIRATION -COOLED j 
 
 AFTERBURNER WITH A POROUS WALL OF BRAZL^ _, 
 AND ROLLED WIRE CLOTH " G 
 
 
 Eh 
 
 By William K. Koffel S ^ 
 
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 ^ ^ 
 
 Lewis Flight Propulsion Laboratory fi § ** 
 
 Cleveland, Ohio o 
 
 ^ H ^ 
 
 UNIVERSITY OF FLORIDA ^ ^ ^ 
 
 DOCUMENTS DEPARTMENT I ^ S 
 
 1 20 MARSTON SCIENCE UBRARY S^ ? § 
 
 P.O. BOX 117011 M ^ g 
 
 GAINESVILLE. FL 32611-7011 USA S g 
 
 Tttlii nmwtiHnt ~"tt->ifrf ■WrrT°fr~ »'«»"«*>t •^- i^Mtonal Defense at the. IJntiet Stalin w.ttjijn, th» measfea 
 
 I 
 
 NATIONAL ADVISORY COMMITTEE 
 FOR AERONAUTICS 
 
 WASHINGTON 
 
 August 19, 1954 
 
 S3NFIDEI<f:riAI^ 
 
,^^^7' -7^3 3&osv?r 
 
 NACARM E54E25 CONFIDENTIAL 
 
 MTIORAL ADVISORY COMMITTEE FOR AERONAUTICS 
 
 RESEARCH MMORANDUM 
 
 COOLING CHARACTERISTICS OF A TRANSPIRATION-COOLED AFTERBURNER WITH A 
 POROUS WALL OF BRAZED AND ROLLED WIRE CLOTH 
 By William K. Koffel 
 
 SUMMARY 
 
 Cooling data were obtained for a transpiration- cooled afterburner 
 having a porous combustion- chamber wall of brazed and rolled wire cloth 
 for a range of exhaust-gas temperatures from 1200° to 3340° R, total 
 flow ratio of cooling air to combustion gas of 0.025 to 0.106, and 
 pressure altitudes of 15,000 to 45,000 feet. The data are successfully 
 correlated over a range of Reynolds number from 75,000 to 1,500,000, 
 based on the distance downstream of the leading edge of the porous wall. 
 
 Maximum wall temperatures based on the cooling correlation were 
 determined for a porous wall of uniform permeability at sea- level take- 
 off and for flight Mach numbers of 0.8, 1.5, and 2.0 at an altitude of 
 35,000 feet. The cooling-air requirements were nearly independent of 
 the flight conditions. A total flow ratio of cooling air to combustion 
 gas of about 0.032 can maintain a maximum wall temperat\are of 1210° R 
 with an exhaust -gas temperatiJre of 3700° R. The total flow ratios with 
 a uniform permeability distribution and air flows sufficient to limit 
 the maximum wall temperatures to 1210° R are about 15 percent higher than 
 the .minimum total flow ratios corresponding to a variable -permeability 
 wall with a constant wall temperature of 1210° R. The total flow ratios 
 for a maximum wall temperature of 1210° R with a wire -cloth afterburner 
 are about 16 percent of the total flow ratios required to cool a 
 stainless-steel afterburner wall convectively to a maximum wall tempera- 
 ture of 1760° R with exhaust-gas temperatures of 3200° and 3700° R. 
 The analysis of cooling-air reqmrements for the previously mentioned 
 flight conditions indicated that cooling-air static pressures must be 
 closely controlled, especially at a flight Mach number of 2.0. 
 
 INTRODUCTION 
 
 The satisfactory cooling of high-thrust-augmentation afterburners 
 for supersonic aircraft requires large amounts of cooling air. These 
 large quantities of cooling air, whether supplied from the ambient-air 
 
 CONFIDENTIAL 
 
CONFIDENTIAL MCA EM E54E25 
 
 stream or from compressor bleed, involve large losses in net thrust. 
 These losses, however, can be .minimized through the use of more effective 
 cooling methods. Transpiration cooling has been shown theoretically 
 (ref . l) to be more effective than film cooling or the conventional 
 method of afterburner cooling by forced convection. The high effective- 
 ness of transpiration cooling was experimentally verified in a preliminary 
 investigation of a transpiration-cooled afterburner having a wall of 
 sintered porous stainless steel (ref. 2). The commercial sintered porous 
 stainless steel used in the preliminary investigation of transpiration 
 cooling for afterburners was unsuitable for use in flight afterburners 
 because of low strength-to-weight ratio, poor control over the uniformity 
 of permeability, and fabrication difficulties. 
 
 In the search for more suitable porous materials, wire cloth was 
 investigated (ref. 3) because of its high strength-to-weight ratio, 
 availability in large sheets, ease of fabrication, and low cost compared 
 with sintered porous metals. The NACA Lewis laboratory designed and 
 built a transpiration-cooled afterburner with a porous wall of the 
 brazed and rolled- wire cloth, described in reference 3. This burner was 
 operated on a turbojet engine to determine the feasibility of a wire-cloth 
 transpiration-cooled afterburner and to evaluate its cooling performance. 
 
 The cooling data from the xd.re-cloth afterbijrner are reported herein 
 for pressure altitudes of 15,000 to 45,000 feet, exhaust-gas temperatures 
 from 1200° to 3340° R, and total flow ratios of cooling air to combustion 
 gas of 0.025 to 0.106. A cooling correlation is derived from these data. 
 This correlation is then used to predict the cooling-air requirements of 
 this afterburner with exhaust-gas temperatures of 3200° and 3700° R for 
 several typical flight conditions of a supersonic airplane. A comparison 
 is also made between the cooling-air reqaairements of this afterburner 
 with transpiration cooling and with conventional forced-convection cooling. 
 The experimental cooling correlation is briefly compared with the 
 approximate theory of Rannie and FiTLedraan (refs. 4 and 5) for transpi- 
 ration cooling with turbulent boundary- layer flow. 
 
 APPARATUS AND INSTRUMENTATION 
 
 Test Installation 
 
 The wire-cloth afterburner was mounted on a conventional axial-flow 
 turbojet engine installed in an altitude test chamber. The test installa- 
 tion aft of the t-urbine flange is shown in figure 1. The engine and 
 afterburner assembly were mounted on a bed plate suspended in the altitude 
 chamber in such a manner as to permit the measurement of jet thrust. A 
 sectional view of the afterburner is shown in figure 2 together with 
 details of the flame holder and fuel- spray bars. The configioration between 
 
 CONFIDENTIAL 
 
 I 
 
MCA EM E54E25 COMFIDENTEAL 
 
 the tiirlDine flange and the heginning of the porous wall^ including the 
 fuel-spray "bars and flame holder, was identical with the high-performance 
 afterbiimer configuration of reference 6, which was evolved from con- 
 figuration C of reference 7. 
 
 Cooling air from an independent soiorce was filtered through 100 
 square feet of 1-inch-thick Fiberglas filter media that retained particles 
 greater than 1 micron. The flow was measiared by means of an A.S.M.E. 
 standard thin-plate orifice. The plenum chamber and the high -temperature 
 impermeable wall upstream of the porous-wall section were Inconel, and 
 the cooling- air side of the .mild steel shroud was painted with zinc 
 chro,mate primer in order to eliminate the possibility of clogging the 
 wire cloth with fine scale. 
 
 The engine fuel was clear unleaded gasoline of 62-octane rating, 
 and the afterburner fuel was MIL-F-562'tA, grade JP-4. 
 
 Wire -Cloth Porous Wall 
 
 The porous combustion- chamber wall was made from wire cloth that 
 was brazed and rolled, for permeability reasons, as described in reference 
 3. The particular cloth used was monel 21x70 twilled Dutch weave 
 (designated cloth B in ref . 3) sprayed with three coats of silver solder 
 per side and brazed and rolled to a 35-percent reduction in original 
 thickness. The average final thickness was 0.0274 inch, and the average 
 permeability coefficient K was about 1x10"° square inch. The tapered 
 combustion chamber was lined with a porous wall made from 20 pieces of 
 wire cloth formed into shallow channels. Each channel was 1/2 inch deep 
 by about 41 inches long and tapered in width from about 4 inches at the 
 upstream end to about 3.5 inches at the downstream end. The channels 
 were spot -welded to angles (fig. 3) that were fastened to the structural 
 shroud by blind rivets. The permeability of each channel differed 
 slightly from the average permeability for all the channels . It was 
 expected that the cooling-air static pressure would vary somewhat 
 circumferentially because of the tangential inlet to the plenum chamber. 
 Therefore, the channels were arranged in an order that would tend to 
 produce a circumferentially uniform distribution of cooling air. 
 
 The newly fabricated porous combustion- chamber wall is shown in 
 figure 4(a) . The channels of wire cloth were permanently biilged toward 
 the center line of the combustion chamber after the initial operation of 
 the engine. Figure 4(b) shows the bulged channels at the end of the 
 cooling investigation with cooling passage heights of about 3/4 to 7/8 
 inch in midchannel. The method of suspending the wire cloth caused a 
 minimimi of disturbance to the cooling-air film on the gas side of the 
 porous wall, and the bulging of the channels reduced tensile stresses 
 in the wire cloth caused by pressure forces. The impermeable wall 
 
 CORFIDEWTIAL 
 
4 COKFIDENTIAL NACA EM E54E25 
 
 upstream of the porous wall was forced-convection cooled by the cooLLng 
 air before it flowed into the 20 dead-ended cooling-air passages. 
 
 Instrumentation 
 
 The research instrumentation for .measurement of temperatures and 
 pressures at" several stations through the turbojet engine was the same 
 as in reference 6. The location of each temperat\ire and pressure 
 measurement on the afterbiirner is shown in figure 5. The five principal 
 stations of instrumentation on the porous wall were 24, 32.6, 41, 49.6, 
 and 57.5 inches downstream of the quick-disconnect flange at the 
 combustion-chamber inlet (see fig. 2) . 
 
 Details of a typical group of instrumentation are shown in figure 6. 
 The cooling-air temperature probes had butt -welded iron-constantan 
 thermocouple junctions shaved smooth to 0.010-inch diameter. Q?he 
 thermocouples on the wire cloth were 28-gage (0.013-in.) chromel-alumel 
 wire individually wrapped with silicone-treated asbestos insulation and 
 overbraided with Fiberglas insulation. The orientation and application 
 of the spot -welded junctions on both sides of the wire cloth can be seen 
 in figure 6. There were only four thermocouples on the gas side of the 
 wire cloth because of difficulties in installation. The shroud tempera- 
 tures were measured with 22-gage (0.025-in.) iron-constantan thermo- 
 couples (not shown in fig. 6) spot-welded to the outside of the shroud. 
 The longitudinal profile of static pressure in the combustion chamber 
 was determined by means of 0.080-inch outside diameter by 0.010-inch 
 wall stainless -steel tubes sweat-brazed into the wire cloth and ground 
 flush. The flexibility of these tubes and the method of leading them 
 out of the passage permitted the wire cloth to assume a natural curve 
 with minimum distortion of the cloth at the point of pressure measurement. 
 
 Strain-gage pressure pickups were mounted on the cooling-air plenum 
 chamber and on the combustion-chamber wall at the flame-holder station 
 to obtain the static -pressure pulsations in the cooling air and combustion 
 chamber diuring ignition and normal afterburning. The pressure pulsations 
 were recorded on a two-channel oscillograph. 
 
 TEST PEOCEDURE 
 
 Air-flow calibrations were obtained for each piece of wire cloth 
 before fabrication into the porous wall. These calibrations were talcen 
 at points where temperature instrumentation was later applied. Add;Ltional 
 cold-alr-flow calibrations were made of the assembled porous wall, as a 
 whole, at several ambient pressure levels before and diiring the cooling 
 investigation to detect any over-all change in the air-flow calibrations 
 from plugging by fuel or combustion residues or from oxidation of the 
 
 CONFIDENTIAL 
 
NACA RM E54E25 
 
 CONFIDENTIAL 
 
 brazing alloy. Nonafterbxjrning check points were also made during the 
 cooling investigation as a check on instrumentation and changes in the 
 wire cloth. 
 
 The data are presented in tables I to V, and the approximate range 
 of some of the variables are given in the following table for an inlet 
 cooling-air temperature of 535° R: 
 
 Pressure 
 altitude, 
 ft 
 
 Compressor 
 air flow, 
 lb/sec 
 
 Cooling -air 
 flow, W^, 
 
 lb/ sec 
 
 Exhaust - 
 gas total 
 temper at \ire , 
 
 °R 
 
 Type of test 
 
 Sea level 
 15,000 
 35,000 
 45,000 
 
 
 
 
 
 
 0.970-5.810 
 1.255-4.344 
 .903-2.849 
 1.49-1.79 
 
 ^535 
 ^535 
 ^535 
 ^535 
 
 Check on air- 
 flow calibration 
 and plugging of 
 wire cloth 
 
 15,000 
 35,000 
 
 45.8 
 25.5 
 
 1.2-3.8 
 .83-2.7 
 
 1200 
 1250 
 
 Cooling, non- 
 afterburning 
 
 15,000 
 35,000 
 45,000 
 
 45.8 
 25.5 
 15.6 
 
 1.37-3.25 
 1.26-3.16 
 1.49-1.79 
 
 2580-3010 
 
 1800-3340 
 
 3185 
 
 Cooling, 
 afterburning 
 
 Approximate ambient -air temperature. 
 
 The cooling-air flow was varied at a given pressixre altitude and 
 fuel-air ratio between the following limits: 
 
 (1) Minimum static -pre ssiore difference Ap across upstream edge of 
 
 wire cloth of 0.5 Ib/sq in. to prevent reverse flow of 
 combustion gas through wire cloth 
 
 (2) Maximum Ap across downstream edge of wire cloth of 6 Ib/sq in. 
 
 to avoid bursting channels of wire cloth 
 
 (3) Maximum wire-cloth temperature of 1460° R to avoid excessive 
 
 rate of plugging from oxidation of silver solder 
 
 (4) Maximum turbine -outlet gas temperature of 1625° R to protect 
 
 turbine from over -temperature 
 
 COMFIDENTIAL 
 
CONFIDENTIAL 
 
 NACA EM E54E25 
 
 (Symbols rixe defined in appendix A.) The ordinate 
 
 METHODS OF CALCULATION AND ANALYSIS 
 
 Cooling -Air Flow 
 
 Local values of the cooling-air flow normal to a unit of wire-cloth 
 surface area (pV)g^ were computed for two channels^ channel 1 having the 
 hottest and'Channel 9 having the coldest porous-wall temperatures. This 
 computation was "based on the air-flow calibrations of figure 1 , the 
 thickness of each channel, the respective longitudinal profiles of 
 cooling-air static pressure, and the assumption that the longitudinal 
 profile of combustion- gas static pressure was circuraferentially uniform. 
 
 T \\x / T 
 figure 7 is in effect a measure of the pressure drop per unit thickness 
 
 across the porous wall, and the abscissa (pV) — is the reduced weight 
 
 flow of cooling air per unit of wire-cloth surface area. The viscosity 
 
 and temperature ratios, ^ /n and (p. /\i) T^/T, reduce the air-flow data 
 
 to NACA standard temperatvire . A theoretical analysis in reference 8 
 indicates that the profile of air temperature across a porous wall 
 should practically coincide with profile of metal temperature except for 
 a very short distance on the side the air enters the wall. Consequently, 
 the viscosity- and temperature -ratio factors should be evaluated at the 
 average local wall temperature. Measured wall temperatures on either 
 side of the wire cloth in this afterburner were within 20° R of each 
 other, so for convenience the factors were evaluated at the temperature 
 measured by the air-side thermocouples, which were installed at each 
 station of channels 1 and 9 . 
 
 The calculated "uotal cooling-air flows in a later section, Cooling- 
 Air Requirements Calculated from Cooling Correlation, were obtained from 
 the step-by-step summation of TtD(pV) Ax. 
 
 Exhaust -Gas Temperat-ure 
 
 The total temperature of the exhaust gas was calculated from the 
 exhaust -nozzle total pressure Pgs^ measured jet thrust, velocity 
 coefficient, and gas flow by the following equation (ref. 7): 
 
 T. 
 
 y 
 
 (1) 
 
 COKFIDEWITAL 
 
NACA EM E54E25 COKFIDENTIAL 
 
 The values of R were computed according to the method of reference 9, 
 and the jet velocity coefficient was determined to be 0.97 from data 
 presented in reference 10. 
 
 Local Combustion-Gas Temperatures 
 
 Locail values of the combustion-gas total temperature T with 
 afterburning were computed from the empirical equation (ref . 11) 
 
 T - T 
 
 g,X g.l . Jt X' f^y, 
 
 T , - t\ = '^'' 2 - (2) 
 
 g^2 g,l 
 
 where T , is ass\mied equal to the turbine -discharge gas temperature, 
 
 and T^ ^ is the exhaust-gas total temperature. Equation (2) makes 
 
 no allowance for possible hot streaks and implies a uniform transverse 
 profile of combustion-gas temperature. Hot streaks undoubtedly were 
 present, although observation of the combustion color and pattern by 
 means of a periscope directed up the burner axis showed good circumfer- 
 ential uniformity. The transverse temperatixre profile was made as 
 uniform as possible ±n a previous investigation of the radial fuel-air 
 distribution when this same configuration had a convection-cooled 
 impermeable wall. 
 
 For nonaf terburning cooling data, local values of bulk total 
 temperature Tg ^ were assumed equal to the turbine -discharge gas 
 
 temperature T^. ]_. 
 
 Correlation of Cooling Data 
 
 Cooling data from five stations along the two typical channels of 
 
 \-d.Te cloth were correlated by plotting the temperature -difference ratio 
 
 (T - T )/(T - T ) against the coolant-flow ratio (pV) /(pU) for 
 ^ w a'' ^ g a' ° ^^ 'a' ^ g 
 
 constant values of bulk Reynolds number. The flow over the porous wall 
 was believed to be similar to the boundary-layer flow over a flat plate, 
 so that the length used in the Reynolds n\;imber was taken as the distance 
 from the leading edge of the porous wall. Consequently, the temperature- 
 difference ratios and the coolant-flow ratios are local values corre- 
 sponding to the local Reynolds numbers. The viscosity of the combustion 
 gas was assLuned to be the same as for air given in table 2 of reference 
 12 and was evaluated at the film temperature T^. The quantity (pU) 
 
 was assumed identical to the local one -dimensional value of total weight 
 flow per unit of combustion-chamber flow area. 
 
 COKFIDEWTIAL 
 
CONFIDENTIAL 
 
 NACA RM E54E25 
 
 The wall temperat\jre T^ in the temperature -difference ratio 
 
 T^) was measured on the cooling-air side of the wire 
 
 (^w - ^a)/(Tg 
 
 cloth but can he considered practically to represent the wall tempera- 
 ture on the hot-gas side because of the small difference in measured 
 temperatin-es across the wire cloth in this af terbiorner . 
 
 Cooling-Air Requirements Calculated from Cooling Correlation 
 
 The experimental cooling correlation of this investigation was used 
 to calculate the longitudinal profile of porous-wall temperature in this 
 af terb\jrner . The conditions analyzed are given in the following table: 
 
 Flight 
 
 Flight 
 
 Altitude, 
 
 Exhaust -gas 
 
 
 condition 
 
 Mach 
 
 ft 
 
 total 
 
 
 
 number 
 
 
 temperature, 
 °R 
 
 ^g.2, 
 
 A 
 
 
 
 Sea level 
 
 3700 
 
 
 B 
 
 .8 
 
 35,000 
 
 3700 
 
 
 B 
 
 .8 
 
 35,000 
 
 3200 
 
 
 C 
 
 1.5 
 
 35,000 
 
 3700 
 
 
 D 
 
 2.0 
 
 35,000 
 
 3700 
 
 
 The turbine -discharge temperature was 1710° R for all conditions. The 
 cooling-air static pressure and the penneability of the porous wall were 
 assumed to be absolutely unifonn, and the air-flow calibration of the 
 porous wall was assumed to be identical with the mean calibration 
 curve of figure 7. With a uniform permeability, most of the porous wall 
 will be overcooled except for some peak temperat"ure region, which must 
 not exceed the maximum allowable operating temperature of the porous 
 material. The calculated maximtmi wall temperatures were plotted against 
 total flow ratio for each flight condition. It should be kept in mind 
 that wall temperatures calculated from the cooling correlation are 
 assumed to be uniform around the circumference at each station. Usually, 
 a safety factor must be allowed for random hot spots in the porous wall 
 caused by hot streaks in the combustion gas or by local areas that have 
 less than the mean permeability. 
 
 Minimum cooling-air flow . - The minimum cooling- air flow for a 
 given temperature limit results when the wall temperature is m;:intained 
 constant at the maximum allowable operating temperature of the porous 
 material by use of an infinitely variable permeability distribution 
 along the porous wall. The assiomption of a constant wall temperature 
 makes it possible to compute the minimum cooling-air distribution and 
 the minimum total flow ratio directly from the cooling correlation 
 without considering the distributions of permeability that would be 
 
 CONFIDENTIAL 
 
NACA RM E54E25 COKFIDENTIAL 
 
 required to provide the minimum cooling-air distribution. Although it 
 is not practical to vary the permeability distribution for each flight 
 and operating condition in an actual afterburner, the minimum flow 
 ratios are usef \il for reference and for examination of trends . Minimum 
 total flow ratios were therefore also computed for flight conditions A to 
 D with a constant porous-wall temperature of 1210° R. 
 
 Longitudinal profile of combustion-gas static pressure . - The static - 
 pressure profile along the length of the combustion chamber was 
 calculated step-by-step from well-known one -dimensional flow relations 
 for momentum pressure drop in a constant -area duct and the isentropic 
 variation of Mach niomber with area ratio. The friction pressure drop, 
 which was assiimed to be small relative to the momentum pressure loss, 
 was neglected. 
 
 Cooling-air pressijre and temperatixre . - The cooling air was assimied 
 to have been bled from an interstage of the compressor (at a compressor 
 efficiency of 0.85) at a pressure high enough to allow for a pressure 
 drop of 1 pound per square inch through valves and ducting to the 
 upstream edge of the porous wall. The pressure drop across the porous 
 wall was limited to a minimum of 1 pound per square inch for practical 
 control, and to a maj:imum of 6 pounds per square inch to prevent 
 bursting the channels of wire cloth. The cooling-air pressiire and 
 temperature were presijmed to be uniform in all cooling-air passages. 
 Convective heat transfer to the cooling air by the impermeable wall 
 upstream of the porous wall was assumed to raise the air temperature 
 50 above that corresponding to the compressor bleed temperature. 
 
 Cooling-Air Requirements with Forced-Convection Cooling 
 
 Cooling-air req\airements for forced-convection cooling of this 
 afterburner with ram air were calcxilated for exhaust -gas temperatures 
 of 3200° and 3700° R for flight condition B from data in reference 13 
 and the cooling correlation of reference 11. 
 
 RESULTS AMD DISCUSSION 
 
 Typical Data 
 
 Figure 8 shows typical measured circumferential profiles of the 
 cooling-air static pressure and wire-cloth temperature. The static- 
 pressure profiles shown result from the tangential inlet on the plenum 
 chamber and the previously mentioned order of assembling the channels 
 of wire cloth. As would be expected, t:ie temperature profiles are the 
 reverse of the pressure profiles. Figixre 8 shows that channel 1 was 
 generally the hottest and channel 9 the coldest, with or ^■d.thout aJter- 
 birrning. 
 
 COItFIDElNlTIAL 
 
10 CONFIDENTIAL NACA RM E54E25 
 
 Typical longitudinal profiles for the wire-cloth afterburner are 
 shown in figure 9. The importance of eliminating circumferential gradients 
 in cooling-air static pressure and in permeability is obvious from the 
 530° R variation in wall temperature at station 62 in figure 9(a). Part of 
 the circumferential temperature spread in this afterburner would have been 
 averted if there had been no circumferential pressure gi'adient in the 
 cooling air. The pressure gradient could have been reduced by a better 
 plenum-chamber inlet or by cross-flow holes in the angles that supported 
 the channels of wire cloth. Wire cloth more closely meeting the specified 
 permeability co\ild have practically eliminated circumferential variations 
 in wall temperatiire, except for those caused by any hot streaks in the 
 combustion gas. The slight drop in cooling-air temperature (figs. 9(a) 
 and (c)) along the length of the cooling-air passage is due to heat 
 losses through the uninsulated shroud. 
 
 The longitudinal profiles of static pressures on both sides of the 
 porous wall are shown at the top of figures 9(b) and (d) . For the 
 relatively high flow ratios shown (W^^/w of 0.0716 to 0.0951), the 
 
 continuous bleeding of air through the porous wall caused a deceleration 
 of the cooling-air flow and a corresponding rise in static pressure of 
 the cooling air in the flow direction. With the low flow ratios of 
 practical interest, the static pressure of the cooling air was almost 
 independent of passage length. 
 
 The variation of pressure drop across the porous wall with distance 
 
 along the wall is represented by the vertical distance between the static 
 
 pressures of the cooling air and of the combustion gas. The resulting 
 
 longitudinal profiles of coolant-flow ratio (pV) /(pU) are shown in 
 
 a g 
 
 figures 9(b) and (d) . The coolant-flow ratios for channel 9 were 
 considerably higher than for channel 1. The differences in coolant-flow 
 ratios are caused by the differences in permeability and the absolute 
 pressure level in each channel. It is recalled that the air-flow cali- 
 brations of figure 7 indicate (pV) is a function of the difference of 
 
 the squares of the absolute static pressure on both sides of the porous 
 wall instead of the pressure drop alone. Tlie curves of the fraction of 
 total cooling-air flow in each channel are almost linear and nearly 
 identical for channels 1 and 9 (figs. 9(b) and (d) ) . It can be inferred, 
 therefore, that the longitudinal addition of cooling air was almost linear 
 through all the channels of wire cloth. 
 
 Before discussing the cooling correlation, it is of interest to 
 determine whether there vms any progressive change in the air-flow 
 calibration of the wire cloth during the cooling investigation. A dioll 
 greasy smudge formed on the combustion-gas side of the wire cloth in 
 spite of the cooling-air film flowing away from the wire cloth dixring all 
 periods of engine operation. The smudge is visible in figure 10 to the 
 left of the white lines. The areas to the rigtit of the white lines have 
 
 CONFIDENTIAL 
 
WACA RM E54E25 CONFIDENTIAL 11 
 
 been wiped clean with cleansing tissue to show the condition of the 
 wire cloth after 4 hours 10 minutes of afterburning. The smudge caused 
 no discernible effect on air-flow calibration. 
 
 Figure 11 shows the circumferential average static -pressure drop 
 across the porous wall against orifice cooling-air flow for several 
 levels of combustion- chamber pressure at stations 24 and 57.5. The 
 agreement between data taken before and during the cooling investigation 
 was excellent at all stations. On the basis of figure 11 and the close 
 agreement between temperature-difference ratios for nonafterbiorning 
 check points, it is concluded that there was no significant change in 
 the air-flow calibration of the wire cloth during the cooling 
 investigation . 
 
 Cooling Correlation 
 
 The experimental cooling data with afterburning are correlated over 
 a range of Reynolds numbers in figures 12(a) to (f ) • Cooling data 
 obtained from channels 1 (hottest) and 9 (coldest) met, or overlapped, 
 to define a single curve when the Reynolds nimiber was held approximately 
 constant. The mean ciurves drawn through groups of data points having 
 approximately the same Reynolds number are summarized in figirre 12(g) . 
 Within the ranges investigated, neither Reynolds number nor radiation 
 had any marked effect on the correlation of afterburning cooling data 
 for coolant-flow ratios less than about 0.007. Above a coolant-flow 
 ratio of 0.007, the temperature -difference ratio, and hence the porous - 
 wall temperature for fixed cooling-air and gas temperatures, decreased 
 as Reynolds n;imber increased from about 75,000 to 800,000. The curves 
 for Reynolds numbers of 1,000,000 and 1,500,000 lie, respectively, above 
 and below the curve for 800,000. It is probable that in this Reynolds 
 nijmber range, corresponding to stations 49.6 and 57.5, increases in 
 radiant heat transfer tend to counxerbalance increases in the Reynolds 
 number (see ref. l) , althoiigh the radiant heat transfer was calculated 
 to be less than one-tenth of the convective heat transfer. 
 
 A direct comparison between the c\irves of the experimental cooling 
 correlation and those predicted by t}ie approximate theory of references 
 4 and 5 is not entirely realistic because of the different assumptions 
 used with these data and those used for develox^ing the approximate theory. 
 However, a partial comparison is made in appendix B. 
 
 Although nonaf terburning conditions were not of primary importance 
 to the present investigation, the nonafterburning conditions are of 
 somewhat general interest in connection with the heat -transfer process 
 of transpiration cooling. The combustion-gas temperat^ore was almost 
 constant along the length of the combustion chamber diuring nonafter- 
 biirning, and radiation from the gas was negligible because of the low 
 
 CONFIDEI^ITIAL 
 
12 CONFIDENTIAL MCA KM E54E25 
 
 gas temperature and pressures. The nonafterb\irnlng coolxng data are 
 presented in tables I to IV. Nonafterburning cooling data are shown 
 in figure 13 by plotting (T^ - T )/(T - T ) against Reynolds number 
 
 for constant values of (pV) /(pU)p.. Cooling correlation curves for 
 
 Reynolds nijmbers of 10 and 10 (fig. 14) were obtained from a cross 
 plot of figure 13. The curves of figure 14 are similar in shape and 
 magnitude to the afterburning data for comparable Reynolds numbers, 
 as can be seen in figure 15. Although somewhat better cooling is in- 
 dicated by the nonafterburning than by the afterburning data at coolant- 
 flow ratios less than about 0.007, the agreement between af terbiirning 
 and nonaf terbijrning data is considered satisfactory. The agreement 
 probably would have been closer if measiored values had been available 
 of the local combustion-gas temperatures and of (pU)p. near the wall, 
 
 instead of assuming (pU) = W /A . The profiles of (pU) are known to 
 differ between nonafterburning and afterburning conditions. 
 
 Transpiration-Cooling Performance 
 
 Figure 16 is a plot of the calculated maximum wall temperatiore 
 against total flow ratio W^W for the assumed flight conditions A 
 
 to D when operating with an exhaust-gas temperature of 3700° R. It 
 shoiild be emphasized that the air flow through the porous wall is a 
 function of the difference of the squares of the absolute pressures on 
 either side of the wall (see fig. 7) . Hence the magnitude and the 
 longitudinal position of the maximum wall temperature are functions of 
 the profiles of the absolute static pressures and of the combustion-gas 
 temperature. The profiles of absolute static pressure are dependent on 
 the flight condition and the pumping characteristics of the engine used, 
 in addition to pressure losses in the afterburner. For the flight 
 conditions investigated, the maximum wall temperature occurred at the 
 leading edge of the porous wall, except when the cooling-air static 
 press-ure was reduced to 10.85 pounds per square inch absolute. At 
 this pressui'e, the maximum wall temperat\ire moved to about station 49.6. 
 
 Separate curves of maximum wall temperat\xre against total flow ratio 
 were obtained for each flight condition (fig. 16) . The curves closely 
 overlap so that the cooling-air requirements were nearly independent of 
 flight conditions; however, the curves would be separated more if the 
 gas temperature had been widely varied. The operable range of total flow 
 ratio varied with flight condition because of the related minimum and max- 
 imum pressure drops across the porous wall. The upper symbol on each curve 
 corresponds to the assumed minimum pressure drop across the porous wall of 
 1 pound per square inch at the leading edge. The lower symbol corresponds 
 to the assumed maximum pressure drop of 6 pounds per square inch at the 
 trailing edge. The resulting minimum and maximum cooling-air pressures are 
 given in figure 16. With a uniform distribution of cooling-air pressure. 
 
 CONFIDENTIAL 
 
NACA RM E54E25 C0KFIDE1\TTIAL 13 
 
 the range in static pressure for control of cooling-air flow at a given 
 flight condition is then 5 pounds per square inch minus the drop in 
 comliusti on -chamber static pressure along the porous wall. Consequently, 
 large drops in combustion- chamber pressure along the porous wall tend to 
 decrease the range of cooling-air static pressiire for control of 
 cooling-air flow. The control range for cooling-air static pressure 
 varied from 3.70 to 0.66 poimds per square inch, respectively, for 
 flight conditions B and D. Cooling-air pressure must be accurately 
 controlled within this range. For example, at flight condition D, a 
 decrease in cooling-air static pressure of 0.66 poiind per square inch 
 (only 1.85 percent of the absolute cooling-air pressure) causes a 256° R 
 increase in maximum wall temperatiure . 
 
 Greater range could be obtained in cooling-air static pressure by 
 using several layers of wire cloth. This type of construction would 
 permit higher pressure drops across the porous wall and would make pos- 
 sible the control of low flows corresponding to high maximum wall temper- 
 atures without danger of reverse flow through the wall. The peak tempera- 
 ture limit for the porous wall was about 1410° R because of oxidation of 
 the brazing alloy on the wire cloth in this afterburner. Therefore, a 
 temperature of 1210° R is assumed to be safe for the maximum wall temper- 
 atures computed from the cooling correlation. This temperature provides 
 a 200 safety factor for local peak temperatures caused by hot streaks in 
 the combustion gas and from small random areas of the cloth that have less 
 
 than the mean permeability. A total flow ratio W /w of about 0.032 can 
 
 o °- S 
 maintain a maximum wall temperature of 1210 R with an exhaust -gas temper- 
 ature of 3700° R at conditions A to C . Calculations indicated that a 
 maximum wall temperature of 1210° R could also be maintained at condi- 
 tion D by increasing the assumed maximum allowable pressure drop across 
 the wire cloth by about 20 percent (point indicated by the end of the 
 dotted extension). * A visual extrapolation of the curves of figure 16 
 (disregarding pressure limits) to a wire-cloth temperature of 1760° R, 
 which is a representative temperature for a wall of stainless steel, re- 
 sults in a total flow ratio of about 0.018. This value compares favor- 
 ably with the total flow ratio of 0.016 computed in reference 2 for the 
 same maximum wall temperature with a porous wall of sintered stainless 
 steel and an exhaust -gas temperature of about 3800° R. The somewhat more 
 effective cooling indicated for a porous wall of sintered stainless steel 
 in reference 2 may be caused by a more imiform film of cooling air on the 
 sintered wall than that produced by the fewer number of larger pores in 
 the surface of the wire cloth. 
 
 A total flow ratio of 0.032 for flight conditions A to D when 
 using a uniform permeability distribution is about 15 percent higher 
 than the minimum total flow ratio for a constant wall temperature of 
 1210° R which would generally require a different permeability distri- 
 bution for each flight condition. Therefore, the practicability of 
 
 COMFIDEriTIAL 
 
14 CONFIDENTIAL NACA RM E54E25 
 
 using vdre cloth having a nonuniform longitudinal distrihution of 
 permeability^ compromising the variahle permeability distributions 
 required to maintain a constant wall temperature for each of the flight 
 conditions investigated, is questionable. 
 
 Some reductions should be expected in the total flow ratios of 
 transpiration- cooled afterb'urners if, throiigh quality control, the toler- 
 ance on the uniformity of perrneability can be decreased from that of the 
 brazed and rolled wire cloth used. The use of porous materials having 
 sufficient strength and resistance to oxidation at higher operating 
 temperatiure s will also permit a reduction in cooling-air flow. For 
 example, the minimum total flow ratio would decrease about 49 percent 
 if the maximum wall temperatixre could be increased from 1210° to 1760 R, 
 which may be possible for cloth woven from stainless steel or Inconel 
 wires. It is expected that problems due to oxidation of a braze alloy 
 can be solved by the use of high-temperature brazing alloys -under 
 development, or by the substitution of sintering for brazing. 
 
 Comparison of Transpiration and Forced-Convection Cooling 
 
 The cooling-air requirements for transpiration and forced-convection 
 cooling of this afterburner are compared in figure 17 for exhaust -gas 
 temperatiires of 3200° and 3700° R at flight condition B. A typical 
 maximum wall temperatiu-e for a forced-convection-cooled wall of stainless 
 steel is 1760° R. With a maximum wall temperature of 1210° R, or limited 
 by minimum practical pressure drop, for a transpiration-cooled wall of 
 brazed and rolled wire cloth, the total flow ratios with transpiration 
 cooling are about 16 percent of the convective requirements for exhaust- 
 gas temperat-ure s oT 3200° and 3700° R. The corresponding inlet cooling- 
 air temperatures are shown at the top of the figure to be about 635° 
 an.'. 444° R, respectively, for transpiration and forced-convection cooling. 
 The higher temperature v/ith transpiration cooling results from compressor 
 bleed and from heat absorbed in convectively cooling the impermeable wall 
 upstream of the porous wall. 
 
 Pressure Environment of Wire Cloth 
 
 The wire cloth successfully withstood the pressure surges of six 
 afterburner starts and the usual pilLsations in pressure during normal 
 steady- state afterburning. Ignition of the afterbui-ner usually caused 
 surges in combustion- chamber static pressure to peak values of 2 to 5 
 inches of mercury. The surges damped out in less than 1 second to the 
 steady-state values. The surge in combustion-chamber static pressirre 
 caused similar surges in cooling-air static pressure that varied anywhere 
 from 0.2 to 1.0 or 1.5 inches of mercury. These surges dissipated to 
 steady-state values in several seconds. During steady-state operation 
 
 COWIDENTIAL 
 
NACA EM E54E25 CONFIDENTIAL 15 
 
 "both the cooling-air and combustion-chamber pressin-e traces showed 
 background pressure pulsations of 100 cps with a total amplitude of 
 about 0.10 to 0.15 inch of mercury superimposed with peaks up to about 
 1 or 2 inches of mercury total amplitude at roughly 3 cps. The duration 
 of these peaks was about 0.01 second. In one or two instances beats were 
 observed in the trace of combustion-chamber static pressure at a beat 
 frequency of 7 cps with a total amplitude of about 1 to 2 inches of 
 mercixry . 
 
 CONCLUDING REMARKS 
 
 Cooling data were obtained for a transpiration- cooled afterbiomer 
 having a porous combustion-chamber wall of brazed and rolled wire cloth. 
 The data cover a range of exhaust-gas temperature from 1200° to 3340° R, 
 total flow ratio of cooling air to combustion gas of 0.025 to 0.106, 
 and pressiore altitudes of 15,000 to 45,000 feet. The data are success- 
 fully correlated over a range of Reynolds numbers from 75,000 to 1,500,000 
 based on the distance downstream of the leading edge of the porous wall. 
 
 Maxlm'um wall temperatures, based on the cooling correlation, were 
 determined for a porous wall of uniform permeability at sea-level take-off 
 and for flight Mach nimibers of 0.8, 1.5, and 2.0 at an altitude of 35,000 
 feet. The cooling-air requirements were nearly independent of the flight 
 conditions. A total flow ratio of cooling air to combustion gas of about 
 0.032 can maintain a ma^mum wall temperature of 1210° R with an exhaust- 
 gas temperature of 3700° R. Savings in cooling air would, of course, be 
 possible with porous material having a higher allowable maximum wall 
 temperatiore . 
 
 The total flow ratios with a uniform permeability distribution and 
 air flows sufficient to limit the maximum wall temperature to 1210° R 
 are about 15 percent higher than the minimum total flow ratios corre- 
 sponding to a variable -permeability wall with a constant wall tempera- 
 ture of 1210° R. 
 
 The total flow ratios of cooling air to combustion gas for a 
 maximum wall temperature of 1210° R with the wire-cloth afterburner are 
 about 16 percent of the total flow ratios required to convectively cool 
 a stainless- steel afterburner wall to a maximum temperature of 1760° R 
 \-n.th exhaust-gas temperatures of 5200° and 3700° R. 
 
 The analysis of cooling-air requirements for the previously 
 mentioned flight conditions indicated that cooling-air static pressure 
 must be closely controlled, especially at a flight Mach number of 2.0. 
 
 Lewis Flight Propulsion Laboratory 
 
 National Advisory Committee for Aeronautics 
 Cleveland, Ohio, June 11, 1954 
 
 CONTIDEI^ITIAL 
 
16 
 
 CONFIDENTIAL 
 
 NACA RM E54E25 
 
 APPENDIX A 
 
 
 J^m 
 
 ■g;'C 
 
 ^E}^ 
 
 K 
 
 Nu 
 
 P 
 
 Pr 
 
 P 
 
 A(p2) 
 
 SYMBOLS 
 
 The following symbols are used in this report: 
 
 combustion-chamber flow area^ sq in. 
 
 jet velocity coefficient^ measured jet thrust 
 divided by isentropic jet thrust for measured 
 mass flow 
 
 specific heat at constant pressure 
 
 inside diameter of combustion chamber, in. 
 
 measured jet thrust, Ih 
 
 acceleration due to gravity, ft/sec 
 
 convective heat-transfer coefficient that would 
 apply to a solid surface under identical outside 
 flow conditions, Btu/(sec)(sq in.)(°R) 
 
 coefficient of nonluminous heat transfer, 
 Btu/(sec)(sq in.)(°R) 
 
 permeability coefficient, sq in. (defined in 
 eq. (6) of ref. 3) 
 
 distance from flame holder to exhaust-nozzle exit, 
 66 in. 
 
 Nusselt number 
 
 total pressure, Ib/sq in. ahs 
 
 Prandtl number 
 
 static pressure, Ib/sq in. abs 
 
 logio 
 
 A(pf]_(M ^ 
 __ T \n/ T_ 
 
 difference between squares of absolute static 
 pressures on both sides of porous wall, p|^ - 
 lb2/in.^ 
 
 pressure-drop parameter, IVi /in. 
 
 Pg-' 
 
 CONFIDLNl'lAL 
 
WACArsiBM E54E25 ' CONFIDENTIAL 17 
 
 R gas constant, ft-lb/(llD) (°R) 
 
 Re Reynolds number, (pU)g(x - 2l)/ii„ 
 
 T total temperature of a gas or surface temperature of a 
 
 solid, °R 
 
 Te + T. 
 
 T|. film temperature,, - ■ „ ) '^ 
 
 T 
 
 e 
 
 g.x 
 
 o^ 
 
 Tct 1 total temperature at combustion- chamber inlet, R 
 Tg 2 total temperature of exhaust gas at nozzle exit, °R 
 Tq NACA standard sea- level temperature, 518.4° R 
 
 temperature -difference ratio 
 
 Tg - Ta 
 
 U velocity in axial-flow direction, in. /sec 
 
 V velocity normal to porous-wall surface, in. /sec 
 
 W weight flow, lb/ sec 
 
 ^a/^g total flow ratio 
 
 X distance downstream of quick-disconnect coupling at 
 
 combustion- chamber inlet, in. 
 
 x' distance downstream of flame holder, x - 2, in. 
 
 Z\x incremental length of combustion chamber, in. 
 
 an- absorptivity of combustion gas 
 
 X„ ratio of specific heats of exhaust gas 
 
 emissivity 
 
 [i. absolute viscosity, lb/(in. ) ( sec) 
 
 p weight density, Ib/cu in. 
 
 (pU)e.x total weight flow per unit of combustion- chamber flow area, 
 
 (Wg + 1] ^alAg^x^ lV( sec) ( sq in. ) 
 
 CONFIDENTIAL 
 
18 COINJFIDENTIAL MCA RM E54E25 
 
 (pV) \JL l\i reduced weight flow per unit area^ lb/(sec)(sq in.) 
 
 (pV)g/(pU) coolant-flow ratio 
 
 T thickness of wire cloth^ in. 
 
 Subscripts: 
 
 a cooling air 
 
 f refers to property evaluated at film temperature T.^ 
 
 g combustion gas 
 
 w wall 
 
 X at distance x 
 
 free-stream conditions 
 
 Numbers greater than 2 represent stations along combustion chamber in 
 inches downstream of quick-disconnect coupling. 
 
 CONFIDENTIAT 
 
NACA RM E54E25 COKFIDENTIAL 19 
 
 APPENDIX B 
 
 COMPARISON OF EXPERIMENTAL COOLING CORRELATION WITH THEORY 
 
 A brief comparison is made between the experimental cooling cor- 
 relation and the approximate theory of Rannie and Friedman (refs. 4 and 
 5) for turbulent boundary-layer flow. The comparison is made between 
 the temperature -difference ratio for individiial data points and the 
 theoretical temperature -difference ratio corresponding to the same ex- 
 perimental conditions. 
 
 The theoretical equation is given by Friedm.an (ref . 5) as 
 
 T - T 
 
 -^w '- a r 
 
 T - T ~ rep 
 
 s a e + r - 1 
 
 (Bl) 
 
 where r is the ratio of the velocity parallel to the s\irface at the 
 border between the lam.inar sublayer and the tiirbulent part of the bound- 
 ary layer to the stream velocity outside the boundary layer. Eckert 
 (ref. 14) gives 
 
 2.11 
 
 (B2) 
 
 (pV)^c^ „ 
 » = ' ^ P^^ (B3) 
 
 H 
 
 For tiirbulent boundary- layer flow over a flat plate, Colb-urn gives 
 
 Nu = 0.0296(Re)°-^(Pr)V3 (B4) 
 
 where Re is based on the distance from the leading edge. Rearranging 
 equation (B4) gives 
 
 RePr - (pu) c - '^TToTzTTTUz ^^-' 
 
 g P,g (Re) (Pr) ' 
 
 from which the local value of convective heat-transfer coefficient at 
 any station :: is 
 
 C01\]FIDEiqTIAL 
 
20 CONFIDENTIAL NACA RM E54E25 
 
 0.0296(pUcp) ^ 
 Hg,c,x = n-^ ^^ (B6) 
 
 g,x' g,x 
 
 The effect of temperature level on the Prandtl n\amber is so small that 
 a mean value was used for all cases. 
 
 The effects of nonluminous radiation were accounted for by substi- 
 tuting the sum of the -equations (B6) and (B7) for H in equation 
 
 (B3). From the data of reference 15, 
 
 0.173 e^ 
 ^g,r,x = (144) (3600) (Tg^^-T^^^) 
 
 e„ „ 1 -SzX 
 
 T^ ^\^ 1% 
 
 S>^ \ 100/ " ^g^x \^ioo / 
 
 (B7) 
 
 where Hg^r x is the heat-transfer coefficient for nonluminous radia- 
 tion at station x. A value of 0.52 was used for the pseudoemissivity 
 6'. The local values of combustion-gas emissivity e and absorptiv- 
 
 ity a_ „ were based on the total fuel-air ratio and local one- 
 
 dimensional values of temperature and static pressure. No distinction 
 was made between total and static combustion-gas tem.perature , because 
 the Mach numbers in the combustion chamber were low. 
 
 The density and viscosity in the Reynolds nvimber in equation (B6) 
 are usually based on the gas temperature just outside the boundary layer. 
 However, in order to obtain a better correlation of heat-transfer data 
 over a large range of T^/Tp., the combination of equations (B3) and (B6) 
 
 (ignoring radiation) was modified in reference 16 to 
 
 (Re)Q-"(Pr)^/^ (P^)a \ 
 0.0296 (pU)p. T, 
 
 (B8) 
 
 The temperature ratio T^/t^ has the effect of evaluating the density 
 °nd viscosity in the Reynolds number at the wall temperat\xre . 
 
 In view of equation (B8), the following equation was deriver! for (p^\ 
 
 w,x 
 <P = '■ 
 
 '^g^x o,0296(pUc^) 0.173 c' 
 
 y s X s 
 
 (Re)0-2(Pr)2/3 " (144)(3600)(T -T ) 
 g>x' 'g,x =" ' 
 
 m \4 
 
 g>x \ioo / g,x \ 100 
 
 (B9) 
 
 CONFIDENTIAL 
 
MCA RM E54E25 COKFIDENTIAL 21 
 
 Equation (B9) was used in equation (B1) and found to overcorrect 
 the theoretical temperature -difference ratio, so that the intermediate 
 temperature ratio T /t was used in the comparison figures 18 
 
 and 19. With afterburning, the inclusion of T^ x/'^f x ■^'^ equation 
 
 (B9) results in theoretical wall temperatures generally higher 
 (fig. 18(a)) than those measured. When a value of 1 is assumed for 
 Tw x/Tf x> "the theoretical wall tenrperatures are lower than those meas- 
 ured and the scatter is less (fig. 18(h)). 
 
 For the nonafterburning data, the inclusion of T^ x/'^f x ^^ 
 
 equation (B9) results in theoretical wall temperatures that are equal 
 to or slightly lower than those measiored (fig. 19(a)). The assumption 
 of T^ x/'^f X °-^ -'- results in a slight lowering of the theoretical 
 wall temperatures over the entire range of temperature -difference 
 ratio (fig. 19(b)), 
 
 The determination of an empirical coefficient or exponent for 
 T^ x/'^f X ^° produce a better agreement does not appear warranted be- 
 cause of differences in the assumptions made in the theory and condi- 
 tions in the afterburner. Therefore, no conclusion is made as to the 
 validity of including the temperature ratios T^ x/'^f x '-'■'^ '^w x/'^a x 
 in the equation for (p. 
 
 REFERENCES 
 
 1. Eckert, E. R. G. , and Livingood, John N. B. : Comparison of Effec- 
 
 tiveness of Convection-, Transpiration-, and Film-Cooling Methods 
 with Air as Coolant. NACA TN 3010, 1953. 
 
 2. Koffel, William K. : Preliminary Experimental Investigation of 
 
 Transpiration Cooling for an Afterburner with a Sintered, Porous 
 Stainless-Steel Combustion-Chamber Wall. NACA RM E53D08, 1953. 
 
 3. Koffel, William K. : Air -Flow Characteristics of Brazed and Rolled 
 
 Wire Filter Cloth for Transpiration-Cooled Afterburners. NACA 
 RM E53H24, 1955. 
 
 4. Rannie, W. D. : A Simplified Theory of Porous Wall Cooling. Prog. 
 
 Rep. 4-50, Power Plant Lab. Proj. No. MX801, Jet Prop. Lab., 
 C.I.T. Nov. 24, 1947. (AMC Contract No. W-535-ac-20260, Ord. 
 Dept. Contract No. W-04-200-0RD-455. ) 
 
 5. Friedman, Joseph: A Theoretical and Experimental Investigation of 
 
 Rocket-Motor Sweat Cooling. Jour. Am. Rocket See, no. 79, Dec. 
 1949, pp. 147-154. 
 
 CONFIDENTIAL 
 
22 CONFIDENTIAL NACA FiM E54E25 
 
 6. Huntley, S. C, Auble, Carmon M. , and Useller, James W. : Altitude 
 
 Performance Investigation of a High -Temperature Afterburner. NACA 
 RM E53D22, 1953. 
 
 7. Conrad, E. William, and Campbell, Carl E. : Altitude Wind Tunnel In- 
 
 vestigation of High-Temperature Afterburners. NACA RM E51L07 , 1952. 
 
 8. Weinba\mi, S., and Wheeler, H. L. , Jr.: Heat Transfer in Sweat- 
 
 Cooled Porous Metals. Prog. Rep. 1-58, Air Lab. Proj. No. MX121, 
 Jet Prop. Lab., C.I.T., Apr. 8, 1947. (AMC Contract No. 
 W-535-ac-20260, Ord. Dept. Contract No. W-04-200-0RD-455. ) 
 
 9. Pinkel, Benjamin, and Turner, L. Richard: Thermodynamic Data for 
 
 the Computation of the Performance of Exhaust-Gas Turbines. NACA 
 WR E-23, 1944. (Supersedes NACA ARE 4B25.) 
 
 10. Wallner , Lewis E., and Wintler, John T. : Experimental Investiga- 
 
 tion of Typical Constant- and Variable-Area Exhaust Nozzles and 
 Effects on Axial -Flow Turbojet-Engine Performance. NACA RM 
 E51D19, 1951. 
 
 11. Koffel, William K. , and Kaufman, Harold R.: Empirical Cooling 
 
 Correlation for an Experimental Afterburner with an Annular 
 Cooling Passage. NACA RM E52C13, 1952. 
 
 12. Keenan, Joseph H. , and Kaye, Joseph: Gas Ta.bles. John V/iley & 
 
 Sons, Inc., 1948. 
 
 13. Koffel, William K. , and Kaufman, Harold R.: Cooling Characteris- 
 
 tics of an Experimental Tail-Pipe Burner with an Annular 
 Cooling -Air Passage. NACA RM E51K23, 1952. 
 
 14. Eckert, E. R. G. : Introduction to the Transfer of Heat and Mass. 
 
 McGraw-Hill Book Co., Inc., 1950. 
 
 15. Mc Adams , William H. : Heat Transmission. Second ed. , McGrnvr- 
 
 Hill Book Co., Inc., 1942, pp. 64-69. 
 
 16. Esgar, Jack B. : An Analytical Method for Evaluating Factors 
 
 Affecting Application of Transpiration Cooling to Gas .Turbine 
 Blades. NACA RM E52G01, 1952. 
 
 1 
 
 COtFIDENTTAL 
 
MCA EM E54E25 
 
 CONFIDENTIAL 
 
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24 
 
 CONFIDENTIAL 
 
 NACA EM E54E25 
 
 TABLE II. - COMBUSTION-CHAMBER WALL TEMPERATURES, °F 
 
 Series 
 
 Channel 
 
 Solid 
 
 metal 
 
 
 Wire-cloth porous wall 
 
 and run 
 
 
 wall 
 
 
 
 
 
 
 ^w,10 
 
 Tw,19 
 
 Tw,24 
 
 '^w,32.6 
 
 ^w,41 
 
 Tw,49.6 
 
 '^w,57.5 
 
 127-27 
 
 1 
 
 558 
 
 553 
 
 429 
 
 459 
 
 443 
 
 419 
 
 400 
 
 
 9 
 
 588 
 
 530 
 
 459 
 
 422 
 
 366 
 
 323 
 
 358 
 
 127-26 
 
 1 
 
 543 
 
 533 
 
 412 
 
 422 
 
 410 
 
 389 
 
 370 
 
 
 9 
 
 570 
 
 512 
 
 420 
 
 382 
 
 331 
 
 293 
 
 330 
 
 127-25 
 
 1 
 
 499 
 
 489 
 
 348 
 
 338 
 
 326 
 
 310 
 
 300 
 
 
 9 
 
 524 
 
 464 
 
 338 
 
 292 
 
 254 
 
 231 
 
 265 
 
 127-24 
 
 1 
 
 468 
 
 449 
 
 302 
 
 282 
 
 270 
 
 260 
 
 250 
 
 
 9 
 
 490 
 
 429 
 
 283 
 
 239 
 
 210 
 
 193 
 
 220 
 
 127-23 
 
 1 
 
 429 
 
 411 
 
 268 
 
 240 
 
 228 
 
 213 
 
 212 
 
 
 9 
 
 452 
 
 392 
 
 240 
 
 198 
 
 183 
 
 160 
 
 181 
 
 127-28 
 
 1 
 
 428 
 
 409 
 
 269 
 
 240 
 
 229 
 
 219 
 
 213 
 
 
 9 
 
 451 
 
 393 
 
 240 
 
 198 
 
 186 
 
 160 
 
 182 
 
 127-21 
 
 1 
 
 600 
 
 549 
 
 437 
 
 462 
 
 460 
 
 434 
 
 422 
 
 
 9 
 
 610 
 
 534 
 
 422 
 
 388 
 
 346 
 
 312 
 
 339 
 
 127-20 
 
 1 
 
 567 
 
 518 
 
 394 
 
 407 
 
 406 
 
 379 
 
 362 
 
 
 9 
 
 583 
 
 499 
 
 372 
 
 331 
 
 293 
 
 263 
 
 287 
 
 130-17 
 
 1 
 
 557 
 
 514 
 
 372 
 
 355 
 
 347 
 
 321 
 
 322 
 
 
 9 
 
 568 
 
 489 
 
 338 
 
 302 
 
 287 
 
 252 
 
 273 
 
 127-17 
 
 1 
 
 538 
 
 503 
 
 367 
 
 372 
 
 368 
 
 339 
 
 333 
 
 
 9 
 
 568 
 
 482 
 
 338 
 
 295 
 
 261 
 
 236 
 
 256 
 
 127-22 
 
 1 
 
 544 
 
 500 
 
 367 
 
 373 
 
 365 
 
 343 
 
 332 
 
 
 9 
 
 568 
 
 481 
 
 337 
 
 294 
 
 260 
 
 219 
 
 265 
 
 130-24 
 
 1 
 
 569 
 
 518 
 
 376 
 
 364 
 
 354 
 
 330 
 
 330 
 
 
 9 
 
 576 
 
 493 
 
 347 
 
 310 
 
 289 
 
 262 
 
 282 
 
 128-4 
 
 1 
 
 839 
 
 815 
 
 810 
 
 725 
 
 780 
 
 745 
 
 850 
 
 
 9 
 
 686 
 
 802 
 
 719 
 
 677 
 
 762 
 
 885 
 
 823 
 
 129-18 
 
 1 
 
 542 
 
 509 
 
 371 
 
 360 
 
 348 
 
 329 
 
 324 
 
 
 9 
 
 370 
 
 482 
 
 338 
 
 298 
 
 279 
 
 242 
 
 267 
 
 129-7 
 
 1 
 
 532 
 
 496 
 
 366 
 
 353 
 
 342 
 
 325 
 
 322 
 
 
 9 
 
 558 
 
 473 
 
 326 
 
 288 
 
 259 
 
 237 
 
 259 
 
 129-32 
 
 1 
 
 539 
 
 510 
 
 372 
 
 359 
 
 346 
 
 327 
 
 324 
 
 
 9 
 
 566 
 
 483 
 
 338 
 
 296 
 
 280 
 
 244 
 
 270 
 
 127-18 
 
 1 
 
 484 
 
 433 
 
 297 
 
 288 
 
 272 
 
 251 
 
 243 
 
 
 9 
 
 502 
 
 413 
 
 255 
 
 213 
 
 192 
 
 176 
 
 192 
 
 CONFIDENTIAL 
 
MCA EM E54E25 
 
 CONFIDEMTIAL 
 
 25 
 
 T^siLE II. - Continued. COMBUSTION-CHAMBER WALL TEMPERATURES, °F 
 
 Series 
 
 Channel 
 
 Solid 
 
 metal 
 
 
 Wire-cloth porous wall 
 
 and run 
 
 
 wall 
 
 
 
 
 
 
 ^w,10 
 
 '^M,19 
 
 '^w,24 
 
 ^w,32.6 
 
 '^w,41 
 
 '^w,49.6 
 
 ^w,57.5 
 
 127-19 
 
 1 
 
 454 
 
 401 
 
 264 
 
 249 
 
 232 
 
 219 
 
 207 
 
 
 9 
 
 470 
 
 388 
 
 220 
 
 182 
 
 172 
 
 151 
 
 163 
 
 129-25 
 
 1 
 
 648 
 
 662 
 
 596 
 
 649 
 
 680 
 
 703 
 
 768 
 
 
 9 
 
 669 
 
 625 
 
 519 
 
 478 
 
 456 
 
 384 
 
 458 
 
 129-26 
 
 1 
 
 649 
 
 669 
 
 608 
 
 669 
 
 699 
 
 728 
 
 790 
 
 
 9 
 
 672 
 
 632 
 
 540 
 
 499 
 
 488 
 
 397 
 
 476 
 
 129-24 
 
 1 
 
 628 
 
 640 
 
 560 
 
 599 
 
 622 
 
 648 
 
 700 
 
 
 9 
 
 648 
 
 600 
 
 481 
 
 433 
 
 420 
 
 359 
 
 429 
 
 129-23 
 
 1 
 
 618 
 
 630 
 
 552 
 
 581 
 
 611 
 
 642 
 
 686 
 
 
 9 
 
 640 
 
 599 
 
 451 
 
 403 
 
 391 
 
 334 
 
 401 
 
 130-37 
 
 1 
 
 598 
 
 605 
 
 506 
 
 552 
 
 582 
 
 577 
 
 602 
 
 
 9 
 
 605 
 
 577 
 
 467 
 
 425 
 
 396 
 
 359 
 
 419 
 
 130-32 
 
 1 
 
 648 
 
 665 
 
 658 
 
 684 
 
 729 
 
 752 
 
 798 
 
 
 9 
 
 662 
 
 649 
 
 556 
 
 506 
 
 452 
 
 403 
 
 467 
 
 130-33 
 
 1 
 
 628 
 
 643 
 
 606 
 
 622 
 
 662 
 
 691 
 
 733 
 
 
 9 
 
 640 
 
 622 
 
 498 
 
 448 
 
 408 
 
 368 
 
 428 
 
 130-31 
 
 1 
 
 622 
 
 632 
 
 586 
 
 608 
 
 631 
 
 638 
 
 665 
 
 
 9 
 
 633 
 
 602 
 
 515 
 
 473 
 
 437 
 
 792 
 
 453 
 
 130-30 
 
 1 
 
 622 
 
 636 
 
 600 
 
 611 
 
 642 
 
 658 
 
 702 
 
 
 9 
 
 688 
 
 608 
 
 500 
 
 454 
 
 418 
 
 375 
 
 437 
 
 130-29 
 
 1 
 
 622 
 
 632 
 
 593 
 
 606 
 
 648 
 
 672 
 
 701 
 
 
 9 
 
 638 
 
 608 
 
 492 
 
 448 
 
 410 
 
 370 
 
 430 
 
 130-34 
 
 1 
 
 664 
 
 681 
 
 692 
 
 751 
 
 823 
 
 877 
 
 890 
 
 
 9 
 
 674 
 
 682 
 
 538 
 
 478 
 
 427 
 
 378 
 
 432 
 
 130-35 
 
 1 
 
 676 
 
 695 
 
 718 
 
 806 
 
 891 
 
 930 
 
 948 
 
 
 9 
 
 682 
 
 707 
 
 551 
 
 488 
 
 436 
 
 382 
 
 438 
 
 130-36 
 
 1 
 
 685 
 
 703 
 
 735 
 
 845 
 
 930 
 
 955 
 
 978 
 
 
 9 
 
 687 
 
 725 
 
 545 
 
 482 
 
 430 
 
 380 
 
 430 
 
 129-21 
 
 1 
 
 379 
 
 577 
 
 457 
 
 468 
 
 478 
 
 478 
 
 505 
 
 
 9 
 
 592 
 
 541 
 
 390 
 
 351 
 
 348 
 
 398 
 
 356 
 
 129-22 
 
 1 
 
 625 
 
 640 
 
 580 
 
 619 
 
 665 
 
 709 
 
 760 
 
 
 9 
 
 653 
 
 650 
 
 417 
 
 362 
 
 352 
 
 299 
 
 355 
 
 129-20 
 
 1 
 
 620 
 
 631 
 
 541 
 
 574 
 
 617 
 
 652 
 
 707 
 
 
 9 
 
 650 
 
 629 
 
 397 
 
 347 
 
 339 
 
 290 
 
 340 
 
 COKFIDEHTIAL 
 
26 
 
 COKFIDENTIAL 
 
 NACA EM E54E25 
 
 TABLE II. - Concluded. COMBUSTION-CHAMBER WALL TEMPERATURES, °r 
 
 Series 
 
 Channel 
 
 Solid 
 
 metal 
 
 
 Wire-cloth po 
 
 rous wall 
 
 and run 
 
 
 wall 
 
 
 
 
 
 
 T 
 w,10 
 
 T 
 w,19 
 
 T 
 w,24 
 
 T 
 w,32.6 
 
 T 
 w,41 
 
 T 
 w,49.6 
 
 T 
 w,57.5 
 
 128-5 
 
 1 
 
 475 
 
 435 
 
 300 
 
 285 
 
 281 
 
 269 
 
 264 
 
 
 9 
 
 489 
 
 422 
 
 262 
 
 220 
 
 215 
 
 187 
 
 214 
 
 128-6 
 
 1 
 
 493 
 
 456 
 
 321 
 
 308 
 
 302 
 
 293 
 
 287 
 
 
 9 
 
 508 
 
 441 
 
 284 
 
 240 
 
 235 
 
 203 
 
 232 
 
 130-20 
 
 1 
 
 690 
 
 678 
 
 564 
 
 629 
 
 666 
 
 689 
 
 759 
 
 
 9 
 
 669 
 
 648 
 
 505 
 
 470 
 
 457 
 
 401 
 
 472 
 
 130-21 
 
 1 
 
 726 
 
 710 
 
 617 
 
 701 
 
 744 
 
 760 
 
 842 
 
 
 9 
 
 721 
 
 676 
 
 588 
 
 572 
 
 527 
 
 490 
 
 558 
 
 130-18 
 
 1 
 
 652 
 
 649 
 
 537 
 
 569 
 
 603 
 
 629 
 
 703 
 
 
 9 
 
 669 
 
 626 
 
 431 
 
 388 
 
 380 
 
 334 
 
 388 
 
 130-19 
 
 1 
 
 670 
 
 662 
 
 544 
 
 589 
 
 627 
 
 654 
 
 727 
 
 
 9 
 
 682 
 
 634 
 
 465 
 
 422 
 
 415 
 
 364 
 
 428 
 
 129-19 
 
 1 
 
 650 
 
 672 
 
 589 
 
 647 
 
 692 
 
 718 
 
 830 
 
 
 9 
 
 696 
 
 690 
 
 425 
 
 368 
 
 352 
 
 302 
 
 354 
 
 129-11 
 
 1 
 
 685 
 
 712 
 
 647 
 
 752 
 
 828 
 
 870 
 
 933 
 
 
 9 
 
 732 
 
 748 
 
 492 
 
 433 
 
 418 
 
 354 
 
 412 
 
 129-10 
 
 1 
 
 662 
 
 689 
 
 600 
 
 680 
 
 738 
 
 713 
 
 857 
 
 
 9 
 
 707 
 
 718 
 
 449 
 
 392 
 
 379 
 
 322 
 
 378 
 
 129-8 
 
 1 
 
 637 
 
 660 
 
 570 
 
 623 
 
 675 
 
 712 
 
 802 
 
 
 9 
 
 678 
 
 677 
 
 408 
 
 353 
 
 344 
 
 297 
 
 340 
 
 129-9 
 
 1 
 
 634 
 
 652 
 
 546 
 
 589 
 
 628 
 
 650 
 
 727 
 
 
 9 
 
 679 
 
 678 
 
 390 
 
 338 
 
 330 
 
 282 
 
 330 
 
 130-27 
 
 1 
 
 709 
 
 720 
 
 611 
 
 682 
 
 751 
 
 778 
 
 842 
 
 
 9 
 
 735 
 
 752 
 
 484 
 
 426 
 
 400 
 
 361 
 
 420 
 
 130-28 
 
 1 
 
 730 
 
 741 
 
 647 
 
 732 
 
 820 
 
 846 
 
 905 
 
 
 9 
 
 751 
 
 774 
 
 519 
 
 464 
 
 432 
 
 393 
 
 449 
 
 130-26 
 
 1 
 
 741 
 
 758 
 
 662 
 
 761 
 
 847 
 
 880 
 
 943 
 
 
 9 
 
 768 
 
 808 
 
 518 
 
 458 
 
 430 
 
 391 
 
 457 
 
 130-25 
 
 1 
 
 753 
 
 787 
 
 679 
 
 803 
 
 900 
 
 926 
 
 986 
 
 
 9 
 
 787 
 
 813 
 
 532 
 
 472 
 
 948 
 
 408 
 
 478 
 
 130-22 
 
 1 
 
 723 
 
 741 
 
 530 
 
 577 
 
 602 
 
 616 
 
 680 
 
 
 9 
 
 769 
 
 798 
 
 472 
 
 420 
 
 392 
 
 362 
 
 426 
 
 130-23 
 
 1 
 
 749 
 
 777 
 
 560 
 
 630 
 
 663 
 
 681 
 
 749 
 
 
 9 
 
 690 
 
 845 
 
 522 
 
 478 
 
 447 
 
 416 
 
 490 
 
 CONFIDENTIAL 
 
HACA EM E54E25 
 
 CONFIDENTIAL 
 
 27 
 
 TABLE III. - COOLING-AIR AND SHROUD TEMPERATURES, °F 
 
 Series 
 and run 
 
 Channel 
 
 
 
 Cool 
 
 ing air 
 
 
 Shroud wall 
 
 '^a,19 
 (a) 
 
 Ta,24 
 
 Ta,32.6 
 
 '^a,41 
 
 ■^3,49.6 
 
 Ta,57.5 
 
 Ts,24 
 
 ■^3,41 
 
 Ts,57.5 
 
 127-27 
 
 1 
 9 
 
 112 
 
 121 
 
 214 
 186 
 
 204 
 179 
 
 195 
 
 185 
 167 
 
 178 
 165 
 
 169 
 
 188 
 
 194 
 
 127-26 
 
 1 
 9 
 
 107 
 117 
 
 200 
 175 
 
 182 
 114 
 
 184 
 
 175 
 157 
 
 166 
 154 
 
 160 
 
 175 
 
 179 
 
 127-25 
 
 1 
 9 
 
 101 
 
 108 
 
 170 
 152 
 
 157 
 108 
 
 157 
 
 150 
 140 
 
 145 
 135 
 
 138 
 
 147 
 
 150 
 
 127-24 
 
 1 
 9 
 
 97 
 103 
 
 152 
 140 
 
 143 
 
 108 
 
 142 
 
 137 
 130 
 
 131 
 125 
 
 126 
 
 133 
 
 133 
 
 127-23 
 
 1 
 9 
 
 94 
 98 
 
 137 
 128 
 
 130 
 107 
 
 131 
 
 127 
 
 122 
 
 120 
 
 117 
 
 116 
 
 124 
 
 121 
 
 127-28 
 
 1 
 9 
 
 94 
 98 
 
 136 
 128 
 
 130 
 123 
 
 130 
 
 127 
 122 
 
 123 
 118 
 
 116 
 
 125 
 
 123 
 
 127-21 
 
 1 
 9 
 
 115 
 125 
 
 213 
 179 
 
 199 
 173 
 
 196 
 
 182 
 166 
 
 174 
 162 
 
 168 
 
 180 
 
 190 
 
 127-20 
 
 1 
 9 
 
 105 
 117 
 
 190 
 160 
 
 178 
 101 
 
 175 
 
 161 
 145 
 
 146 
 138 
 
 150 
 
 157 
 
 155 
 
 130-17 
 
 1 
 9 
 
 104 
 113 
 
 171 
 153 
 
 162 
 151 
 
 159 
 
 153 
 
 140 
 
 132 
 132 
 
 139 
 
 144 
 
 141 
 
 127-17 
 
 1 
 9 
 
 101 
 110 
 
 177 
 152 
 
 167 
 104 
 
 164 
 
 153 
 138 
 
 138 
 132 
 
 140 
 
 148 
 
 147 
 
 127-22 
 
 1 
 9 
 
 106 
 115 
 
 184 
 158 
 
 172 
 105 
 
 170 
 
 162 
 150 
 
 160 
 149 
 
 147 
 
 157 
 
 168 
 
 130-24 
 
 1 
 9 
 
 107 
 117 
 
 175 
 159 
 
 166 
 154 
 
 165 
 
 156 
 144 
 
 144 
 
 141 
 
 144 
 
 151 
 
 154 
 
 128-4 
 
 1 
 9 
 
 97 
 107 
 
 175 
 151 
 
 165 
 149 
 
 163 
 
 152 
 139 
 
 137 
 132 
 
 142 
 
 148 
 
 148 
 
 129-18 
 
 1 
 9 
 
 101 
 112 
 
 170 
 
 151 
 
 161 
 155 
 
 160 
 
 133 
 135 
 
 148 
 126 
 
 138 
 
 144 
 
 138 
 
 129-7 
 
 1 
 9 
 
 99 
 109 
 
 169 
 149 
 
 160 
 143 
 
 158 
 
 
 
 135 
 136 
 
 145 
 131 
 
 136 
 
 142 
 
 140 
 
 129-32 
 
 1 
 9 
 
 104 
 115 
 
 171 
 154 
 
 164 
 155 
 
 163 
 
 144 
 140 
 
 150 
 136 
 
 141 
 
 148 
 
 146 
 
 127-18 
 
 1 
 9 
 
 95 
 101 
 
 149 
 185 
 
 193 
 
 101 
 
 142 
 
 136 
 127 
 
 131 
 123 
 
 123 
 
 130 
 
 131 
 
 Values read from circumferential temperature profiles. 
 
 CONEIDENTIAL 
 
28 
 
 CONFIDENTIAL 
 
 NACA BM E54E25 
 
 TABLE III. - Continued. COOLING-AIR AND SHROUD TEMPERATURES, °F 
 
 Series 
 and run 
 
 Channel 
 
 
 
 Cooli 
 
 ng air 
 
 
 Shroud wall 
 
 Ta,19 
 (a) 
 
 Ta,24 
 
 '''a, 32. 6 
 
 Ta,41 
 
 Ta,49.6 
 
 Ta,57.5 
 
 Ts,24 
 
 ■^3,41 
 
 Ts,57.5 
 
 127-19 
 
 1 
 9 
 
 92 
 
 97 
 
 137 
 127 
 
 133 
 122 
 
 131 
 
 127 
 120 
 
 121 
 115 
 
 115 
 
 121 
 
 120 
 
 129-25 
 
 1 
 9 
 
 126 
 130 
 
 255 
 200 
 
 222 
 213 
 
 229 
 
 242 
 
 181 
 
 224 
 186 
 
 195 
 
 224 
 
 257 
 
 129-26 
 
 1 
 9 
 
 129 
 134 
 
 264 
 207 
 
 228 
 219 
 
 236 
 
 254 
 185 
 
 232 
 192 
 
 200 
 
 232 
 
 273 
 
 129-24 
 
 1 
 9 
 
 122 
 127 
 
 235 
 190 
 
 208 
 200 
 
 214 
 
 224 
 173 
 
 209 
 177 
 
 181 
 
 208 
 
 239 
 
 129-23 
 
 1 
 9 
 
 117 
 122 
 
 223 
 182 
 
 200 
 207 
 
 205 
 
 
 
 210 
 165 
 
 196 
 
 169 
 
 171 
 
 195 
 
 216 
 
 130-37 
 
 1 
 
 9 
 
 112 
 120 
 
 219 
 190 
 
 193 
 181 
 
 198 
 
 195 
 163 
 
 204 
 171 
 
 167 
 
 191 
 
 209 
 
 130-32 
 
 1 
 9 
 
 124 
 125 
 
 265 
 213 
 
 228 
 149 
 
 236 
 
 231 
 
 177 
 
 238 
 185 
 
 194 
 
 227 
 
 256 
 
 130-33 
 
 1 
 9 
 
 119 
 121 
 
 240 
 196 
 
 210 
 141 
 
 217 
 
 216 
 168 
 
 231 
 176 
 
 179 
 
 210 
 
 244 
 
 130-31 
 
 1 
 9 
 
 117 
 122 
 
 241 
 201 
 
 209 
 
 215 
 
 210 
 171 
 
 214 
 180 
 
 180 
 
 206 
 
 226 
 
 130-30 
 
 1 
 9 
 
 117 
 122 
 
 138 
 
 197 
 
 208 
 196 
 
 214 
 
 208 
 168 
 
 211 
 174 
 
 177 
 
 205 
 
 222 
 
 130-29 
 
 1 
 9 
 
 115 
 121 
 
 235 
 194 
 
 207 
 
 131 
 
 213 
 
 210 
 166 
 
 217 
 171 
 
 176 
 
 206 
 
 230 
 
 130-34 
 
 1 
 9 
 
 125 
 124 
 
 264 
 208 
 
 228 
 139 
 
 239 
 
 239 
 174 
 
 256 
 179 
 
 192 
 
 230 
 
 275 
 
 130-35 
 
 1 
 
 9 
 
 127 
 128 
 
 273 
 212 
 
 235 
 137 
 
 248 
 
 249 
 177 
 
 176 
 183 
 
 196 
 
 239 
 
 198 
 
 130-36 
 
 1 
 9 
 
 128 
 128 
 
 274 
 210 
 
 236 
 
 140 
 
 250 
 
 256 
 177 
 
 290 
 183 
 
 198 
 
 246 
 
 315 
 
 129-21 
 
 1 
 9 
 
 107 
 117 
 
 190 
 167 
 
 175 
 166 
 
 176 
 
 178 
 154 
 
 156 
 
 156 
 
 150 
 
 165 
 
 184 
 
 129-22 
 
 1 
 9 
 
 116 
 121 
 
 219 
 174 
 
 211 
 170 
 
 204 
 
 210 
 160 
 
 199 
 161 
 
 169 
 
 191 
 
 218 
 
 129-20 
 
 1 
 9 
 
 114 
 119 
 
 210 
 170 
 
 193 
 165 
 
 197 
 
 203 
 156 
 
 192 
 157 
 
 164 
 
 183 
 
 205 
 
 ^Values read from circumferential temperature profiles. 
 
 CONFIDENTIAL 
 
MCA EM E54E25 
 
 CONFIDENTIAL 
 
 29 
 
 TABLE III. - Concluded. COOLING-AIR AND SHROUD TEMPERATURES, °F 
 
 Series 
 and run 
 
 Channel 
 
 Cooling air 
 
 Shroud wall 
 
 Ta,19 
 (a) 
 
 Ta,24 
 
 ■^3,32.6 
 
 Ta,41 
 
 '^a,49.6 
 
 Ta,57.5 
 
 Ts,24 
 
 Ts,41 
 
 Ts,57.5 
 
 128-5 
 
 1 
 9 
 
 89 
 96 
 
 140 
 131 
 
 135 
 
 130 
 
 134 
 
 130 
 
 122 
 
 121 
 117 
 
 117 
 
 125 
 
 123 
 
 128-6 
 
 1 
 9 
 
 90 
 
 98 
 
 146 
 
 136 
 
 140 
 136 
 
 139 
 
 134 
 127 
 
 124 
 123 
 
 121 
 
 129 
 
 128 
 
 130-20 
 
 1 
 9 
 
 129 
 132 
 
 243 
 197 
 
 253 
 253 
 
 179 
 
 224 
 
 179 
 
 239 
 
 190 
 
 191 
 
 219 
 
 256 
 
 130-21 
 
 1 
 9 
 
 137 
 142 
 
 273 
 218 
 
 248 
 334 
 
 259 
 
 254 
 199 
 
 274 
 214 
 
 217 
 
 256 
 
 303 
 
 130-18 
 
 1 
 9 
 
 117 
 122 
 
 215 
 177 
 
 199 
 170 
 
 203 
 
 194 
 
 158 
 
 186 
 156 
 
 169 
 
 186 
 
 199 
 
 130-19 
 
 1 
 9 
 
 124 
 127 
 
 229 
 
 187 
 
 211 
 182 
 
 216 
 
 211 
 170 
 
 244 
 
 177 
 
 180 
 
 203 
 
 234 
 
 129-19 
 
 1 
 9 
 
 118 
 123 
 
 224 
 177 
 
 220 
 175 
 
 213 
 
 212 
 160 
 
 206 
 158 
 
 173 
 
 197 
 
 220 
 
 129-11 
 
 1 
 9 
 
 124 
 128 
 
 249 
 
 191 
 
 247 
 187 
 
 238 
 
 240 
 175 
 
 236 
 
 172 
 
 191 
 
 224 
 
 275 
 
 129-10 
 
 1 
 9 
 
 118 
 125 
 
 233 
 182 
 
 214 
 197 
 
 220 
 
 228 
 164 
 
 214 
 155 
 
 179 
 
 204 
 
 238 
 
 129-8 
 
 1 
 9 
 
 114 
 119 
 
 217 
 171 
 
 200 
 170 
 
 205 
 
 191 
 154 
 
 195 
 150 
 
 166 
 
 186 
 
 199 
 
 129-9 
 
 1 
 9 
 
 118 
 120 
 
 213 
 170 
 
 195 
 165 
 
 200 
 
 210 
 156 
 
 197 
 157 
 
 164 
 
 
 
 184 
 
 215 
 
 130-27 
 
 1 
 9 
 
 127 
 133 
 
 246 
 198 
 
 226 
 144 
 
 236 
 
 241 
 179 
 
 275 
 190 
 
 192 
 
 225 
 
 293 
 
 130-28 
 
 1 
 9 
 
 129 
 137 
 
 258 
 204 
 
 236 
 
 130 
 
 247 
 
 250 
 179 
 
 279 
 184 
 
 200 
 
 236 
 
 302 
 
 130-26 
 
 1 
 9 
 
 129 
 137 
 
 260 
 205 
 
 239 
 197 
 
 251 
 
 257 
 185 
 
 296 
 
 198 
 
 201 
 
 241 
 
 325 
 
 130-25 
 
 1 
 9 
 
 126 
 137 
 
 256 
 206 
 
 236 
 191 
 
 247 
 
 245 
 
 180 
 
 255 
 
 186 
 
 199 
 
 235 
 
 283 
 
 130-22 
 
 1 
 9 
 
 127 
 
 139 
 
 227 
 198 
 
 212 
 
 185 
 
 216 
 
 209 
 
 173 
 
 219 
 171 
 
 181 
 
 196 
 
 229 
 
 130-23 
 
 1 
 9 
 
 132 
 149 
 
 247 
 
 211 
 
 229 
 201 
 
 235 
 
 233 
 
 198 
 
 258 
 218 
 
 195 
 
 219 
 
 178 
 
 Values read from circumferential temperature profiles. 
 
 CONEIDENTIAL 
 
30 
 
 CONFIDENTIAL 
 
 NACA EM E54E25 
 
 TABLE IV . - C0HBUSTI0N-GA3 AMI) COOLIBG-AIB PRESSURES 
 
 Series 
 and run 
 
 Channel 
 
 Combustion-chamber static pressares, 
 
 Ib/aq In. abs 
 
 
 Coollng-alr pressurea^ 
 
 Ib/eq In. aba 
 
 
 "g.io 
 
 Pg.l9 
 
 I'g,24 
 
 I'g,32.6 
 
 Pg,41 
 
 Pg,49.6 
 
 Pg,57.5 
 
 ''g,63.e 
 
 ''g,67.8 
 
 Pa,15 
 
 ^,24 
 
 Pa,24 
 
 Pa, 32. 6 
 
 Pa,41 
 
 I'a,49.6 
 
 I'a,57.5 
 
 127-27 
 
 1 
 9 
 
 9.507 
 
 9.778 
 
 9.840 
 
 9.688 
 
 9.556 
 
 9.243 
 
 9.18B 
 
 8.715 
 
 8.354 
 
 10.4 
 
 10.29 
 10.42 
 
 10.16 
 10.20 
 
 10.21 
 10.30 
 
 10.21 
 10.31 
 
 10.22 
 10.30 
 
 10.22 
 10.29 
 
 127-26 
 
 1 
 9 
 
 9.493 
 
 9.757 
 
 9.813 
 
 9.660 
 
 9.521 
 
 9.194 
 
 9.132 
 
 8.625 
 
 8.326 
 
 10.62 
 
 10.49 
 10.66 
 
 10.29 
 10.37 
 
 10.37 
 10.51 
 
 10.38 
 10.52 
 
 10.39 
 10.51 
 
 10.38 
 10.50 
 
 127-25 
 
 1 
 9 
 
 9.604 
 
 9.882 
 
 9.910 
 
 9.764 
 
 9.583 
 
 9.257 
 
 9.146 
 
 8.653 
 
 8.319 
 
 11.71 
 
 11.43 
 11.79 
 
 11.03 
 11.27 
 
 11.19 
 11.49 
 
 11.22 
 11.53 
 
 11.23 
 11.52 
 
 11.23 
 11.51 
 
 127-24 
 
 1 
 9 
 
 9.701 
 
 9.979 
 
 9.993 
 
 9.833 
 
 9.625 
 
 9.265 
 
 9.139 
 
 8.646 
 
 8.319 
 
 13.05 
 
 12.49 
 
 13.11 
 
 11.86 
 12.33 
 
 12.14 
 12.65 
 
 12.19 
 
 12.71 
 
 12.20 
 12.70 
 
 12.21 
 12.69 
 
 127-23 
 
 1 
 9 
 
 9.785 
 
 10.06 
 
 10.07 
 
 9.903 
 
 9.660 
 
 9.292 
 
 9.097 
 
 8.681 
 
 8.326 
 
 14.81 
 
 13.95 
 14.87 
 
 13.00 
 13.80 
 
 13.43 
 14.25 
 
 13.51 
 14.34 
 
 13.53 
 14.33 
 
 13.54 
 14.33 
 
 127-28 
 
 1 
 9 
 
 9.785 
 
 10.06 
 
 10.08 
 
 9.903 
 
 9.646 
 
 9.299 
 
 9.104 
 
 8.646 
 
 8.340 
 
 14.70 
 
 13.84 
 
 14.75 
 
 12.86 
 13.67 
 
 13.31 
 14.13 
 
 13.39 
 14.22 
 
 13.42 
 14.22 
 
 13.42 
 14.21 
 
 127-21 
 
 1 
 9 
 
 4.500 
 
 4.708 
 
 4.757 
 
 4.667 
 
 4.576 
 
 4.326 
 
 4.257 
 
 3.854 
 
 3.500 
 
 5.563 
 
 5.48 
 5.57 
 
 5.35 
 5.38 
 
 5.39 
 5.48 
 
 5.39 
 5.49 
 
 5.40 
 5.48 
 
 5.39 
 
 5.46 
 
 127-20 
 
 1 
 9 
 
 4.542 
 
 4.750 
 
 4.778 
 
 4.694 
 
 4.590 
 
 4.340 
 
 4.250 
 
 3.833 
 
 3.479 
 
 6.055 
 
 5.912 
 6.077 
 
 5.700 
 5.790 
 
 5.780 
 5.928 
 
 5.790 
 5.939 
 
 5.795 
 5.93 
 
 5.790 
 5.918 
 
 130-17 
 
 1 
 9 
 
 4.625 
 
 4.84 
 
 4.889 
 
 4.785 
 
 4.646 
 
 4.444 
 
 4.194 
 
 3.931 
 
 3.556 
 
 6.605 
 
 6.397 
 6.647 
 
 6.083 
 6.386 
 
 6.195 
 6.471 
 
 6.216 
 6.482 
 
 6.227 
 6.498 
 
 6.216 
 6.492 
 
 127-17 
 
 1 
 9 
 
 4.569 
 
 4.778 
 
 4.819 
 
 4.715 
 
 4.597 
 
 4.354 
 
 4.250 
 
 3.B75 
 
 3.500 
 
 6.493 
 
 6.301 
 6.536 
 
 6.025 
 6.163 
 
 6.121 
 6.322 
 
 6.142 
 6.344 
 
 6.153 
 6.33 
 
 6.147 
 6.323 
 
 127-22 
 
 1 
 9 
 
 4.563 
 
 4.764 
 
 4.806 
 
 4.708 
 
 4.583 
 
 4.326 
 
 4.222 
 
 3.826 
 
 3.479 
 
 6.514 
 
 6.312 
 6.551 
 
 6.030 
 6.179 
 
 6.136 
 6.349 
 
 6.152 
 6.365 
 
 6.158 
 6.35 
 
 6.158 
 6.338 
 
 130-24 
 
 1 
 9 
 
 4.569 
 
 4.785 
 
 4.826 
 
 4.736 
 
 4.590 
 
 4.389 
 
 4.146 
 
 3.854 
 
 3.465 
 
 6.470 
 
 6.281 
 6.509 
 
 5.973 
 6.260 
 
 6.079 
 6.345 
 
 6.100 
 6.355 
 
 6.105 
 6.366 
 
 6.100 
 6.366 
 
 128-4 
 
 1 
 9 
 
 4.56 
 
 4.78 
 
 4.76 
 
 4.69 
 
 4.58 
 
 4.33 
 
 4.22 
 
 3.82 
 
 3.48 
 
 6.425 
 
 6.191 
 6.414 
 
 5.914 
 6.159 
 
 6.031 
 6.239 
 
 6.042 
 6.265 
 
 6.053 
 
 6.053 
 6.265 
 
 129-18 
 
 1 
 9 
 
 4.576 
 
 4.792 
 
 4.813 
 
 4.750 
 
 4.611 
 
 4.431 
 
 
 3.910 
 
 3.514 
 
 6.61 
 
 6. .39 
 6.65 
 
 6.06 
 6.40 
 
 6.21 
 6.47 
 
 6.22 
 6.48 
 
 6.23 
 6.48 
 
 6.23 
 6.49 
 
 129-7 
 
 1 
 9 
 
 4.715 
 
 4.931 
 
 4.938 
 
 4.840 
 
 4.729 
 
 4.493 
 
 4.354 
 
 3.958 
 
 3.632 
 
 6.82 
 
 6.59 
 6.87 
 
 6.27 
 6.60 
 
 6.39 
 6.68 
 
 6.41 
 6.69 
 
 6.41 
 6.69 
 
 6.41 
 6.70 
 
 129-32 
 
 1 
 9 
 
 4.625 
 
 4.833 
 
 4.854 
 
 4.785 
 
 4.646 
 
 4.465 
 
 6.438 
 
 3.922 
 
 3.611 
 
 6.748 
 
 6.499 
 6.791 
 
 6.175 
 6.515 
 
 6.313 
 6. BOO 
 
 6.329 
 6.610 
 
 6.334 
 6.175 
 
 6.334 
 6.621 
 
 127-18 
 
 1 
 9 
 
 4.701 
 
 4.903 
 
 4.931 
 
 4.806 
 
 4.646 
 
 4.382 
 
 4.208 
 
 3.847 
 
 3.iS8 
 
 8.326 
 
 7.847 
 8.390 
 
 7.326 
 7.746 
 
 7.54.9 
 8.017 
 
 7.592 
 8.060 
 
 7.613 
 8.045 
 
 7.613 
 8.028 
 
 127-19 
 
 1 
 9 
 
 4.806 
 
 5.000 
 
 5.0OO 
 
 4.889 
 
 4.701 
 
 4.417 
 
 4.208 
 
 3.847 
 
 3.431 
 
 9.722 
 
 9.06 
 9.80 
 
 8.34 
 8.99 
 
 8.66 
 9.33 
 
 8.72 
 9.39 
 
 8.74 
 9.38 
 
 8.74 
 9.37 
 
 129-2S 
 
 1 
 9 
 
 14.63 
 
 14.55 
 
 14.39 
 
 13.93 
 
 13.25 
 
 12.65 
 
 
 10.38 
 
 8.382 
 
 15.81 
 
 15.43 
 15.88 
 
 15.02 
 15.47 
 
 15.17 
 15.56 
 
 15.20 
 15.60 
 
 15.23 
 15.60 
 
 15.23 
 15.61 
 
 129-26 
 
 1 
 9 
 
 14.56 
 
 14.51 
 
 14.36 
 
 13.90 
 
 13.23 
 
 12.63 
 
 
 10.36 
 
 8.431 
 
 15.59 
 
 15.25 
 15.66 
 
 14.87 
 15.28 
 
 15.02 
 15.38 
 
 15.04 
 15.39 
 
 15.06 
 15.40 
 
 15.06 
 15.41 
 
 129-24 
 
 1 
 9 
 
 14.65 
 
 14.60 
 
 14.42 
 
 13.97 
 
 13.26 
 
 12.65 
 
 
 10.38 
 
 8.375 
 
 16.23 
 
 15.52 
 16.37 
 
 14.81 
 15.61 
 
 15.08 
 15.82 
 
 15.14 
 
 15.86 
 
 15.16 
 15.87 
 
 15.18 
 15.89 
 
 129-23 
 
 I 
 9 
 
 14.74 
 
 14.65 
 
 14.49 
 
 14.01 
 
 13.28 
 
 12.64 
 
 
 10.40 
 
 8.306 
 
 16.76 
 
 15.89 
 16.92 
 
 15.05 
 16.04 
 
 15.41 
 16.28 
 
 15.48 
 16.34 
 
 15.51 
 16.36 
 
 15.52 
 16.38 
 
 130-37 
 
 1 
 9 
 
 16.04 
 
 16.00 
 
 15.97 
 
 15.47 
 
 14.49 
 
 13.73 
 
 12.76 
 
 
 8.374 
 
 17.46 
 
 17.00 
 17.54 
 
 16.48 
 17.03 
 
 16.67 
 17.18 
 
 16.72 
 17.21 
 
 16.74 
 17.24 
 
 16.74 
 17.24 
 
 130-32 
 
 1 
 9 
 
 16.59 
 
 16.47 
 
 16.42 
 
 15.85 
 
 14.84 
 
 14.09 
 
 12.86 
 
 11.43 
 
 8.333 
 
 17.33 
 
 16.98 
 17.39 
 
 16.59 
 16.99 
 
 16.70 
 17.10 
 
 16.74 
 17.12 
 
 16.76 
 17.14 
 
 16.76 
 16.79 
 
 130-33 
 
 1 
 9 
 
 16.69 
 
 16.55 
 
 16.49 
 
 15.91 
 
 14.88 
 
 14.12 
 
 12.90 
 
 11.50 
 
 8.409 
 
 18.01 
 
 17.53 
 18.08 
 
 17.01 
 17.56 
 
 17.19 
 17.71 
 
 17.23 
 17.74 
 
 17.26 
 17.77 
 
 17.25 
 17.77 
 
 CONFIDENTIAL 
 
MCA EM E54E25 
 
 CONFIDENTIAL 
 
 31 
 
 TABLE IV. - Concluded. COMBUSTION-GAS AMD COOLING-AIR PSESSUPES 
 
 Series 
 and run 
 
 Channel 
 
 Combustion-chafliter static pressures, 
 
 Ib/sq ir 
 
 . abs 
 
 
 
 Coolin8-air pressures 
 
 , Ib/sq 
 
 in. abs 
 
 
 "8,10 
 
 "g,19 
 
 "8,24 
 
 Pg,32.6 
 
 "8,41 
 
 "g,49.6 
 
 "8,57.5 
 
 "8,63.8 
 
 "g,67.a 
 
 Pa,15 
 
 Pa,24 
 
 "a, 24 
 
 "a,32.6 
 
 "a,41 
 
 "a,49.6 
 
 "a,57.5 
 
 130-31 
 
 1 
 9 
 
 15.94 
 
 15.68 
 
 15.85 
 
 15.36 
 
 14.42 
 
 13.69 
 
 12.47 
 
 11.15 
 
 8.340 
 
 16.66 
 
 16.50 
 16.93 
 
 16.08 
 16.52 
 
 15.22 
 16.64 
 
 16.25 
 16.65 
 
 16.27 
 16.67 
 
 15.28 
 16.68 
 
 130-30 
 
 1 
 9 
 
 16.20 
 
 16.11 
 
 16.06 
 
 15.53 
 
 14.55 
 
 13.81 
 
 12.59 
 
 11.27 
 
 8.312 
 
 17.40 
 
 16.95 
 17.46 
 
 16.48 
 17.00 
 
 16.65 
 17.13 
 
 16.68 
 17.15 
 
 16.70 
 17.18 
 
 16.71 
 17.18 
 
 130-29 
 
 1 
 9 
 
 16.26 
 
 16.16 
 
 16.10 
 
 15.56 
 
 14.56 
 
 13.83 
 
 12.61 
 
 12.17 
 
 8.361 
 
 17.52 
 
 17.07 
 17.59 
 
 16.57 
 16.98 
 
 16.74 
 17.25 
 
 16.79 
 17.28 
 
 16.81 
 17.30 
 
 16.82 
 17.31 
 
 130-34 
 
 1 
 9 
 
 17.43 
 
 17.21 
 
 17.11 
 
 16.43 
 
 15.29 
 
 14.53 
 
 13.34 
 
 11.80 
 
 8.381 
 
 18.48 
 
 18.10 
 18.63 
 
 17.60 
 18.11 
 
 17.77 
 18.26 
 
 17.81 
 18.28 
 
 17.63 
 16.31 
 
 17.84 
 18.32 
 
 130-35 
 
 1 
 9 
 
 17.70 
 
 17.45 
 
 17.33 
 
 16.59 
 
 15.42 
 
 14.67 
 
 13.58 
 
 11.94 
 
 8.361 
 
 18.75 
 
 18.29 
 18.82 
 
 17.80 
 18.30 
 
 17.96 
 18.44 
 
 18.01 
 18.47 
 
 16.03 
 18.50 
 
 18.03 
 18.50 
 
 130-36 
 
 1 
 9 
 
 17.94 
 
 17.67 
 
 17.53 
 
 16.76 
 
 16.53 
 
 14.63 
 
 13.81 
 
 12.10 
 
 6.381 
 
 19.18 
 
 18.70 
 19.25 
 
 18.16 
 18.70 
 
 18.35 
 18.85 
 
 18.39 
 16.88 
 
 16.41 
 18.91 
 
 18.41 
 18.91 
 
 189.21 
 
 1 
 9 
 
 11.67 
 
 11.88 
 
 11.77 
 
 11.43 
 
 10.90 
 
 10.36 
 
 
 8.576 
 
 7.153 
 
 14.42 
 
 13.64 
 14.67 
 
 12.75 
 13.79 
 
 13.15 
 14.06 
 
 13.22 
 14.11 
 
 13.25 
 14.13 
 
 13.26 
 14.15 
 
 129-22 
 
 1 
 9 
 
 13.35 
 
 13.20 
 
 13.00 
 
 12.48 
 
 11.78 
 
 11.21 
 
 
 9.153 
 
 7.056 
 
 16.42 
 
 15.33 
 16.60 
 
 14.26 
 15.51 
 
 14.72 
 15.83 
 
 14.60 
 15.89 
 
 14.85 
 15.92 
 
 14.87 
 15.94 
 
 129-20 
 
 1 
 9 
 
 11.18 
 
 11.06 
 
 10.90 
 
 10.45 
 
 9.668 
 
 9.368 
 
 
 7.604 
 
 5.840 
 
 14.54 
 
 13.84 
 14.65 
 
 13.14 
 13.96 
 
 13.45 
 14.16 
 
 13.50 
 14.21 
 
 13.52 
 14.22 
 
 13.53 
 14.23 
 
 126-5 
 
 1 
 9 
 
 6.72 
 
 6.80 
 
 6.72 
 
 6.54 
 
 6.22 
 
 5.78 
 
 5.44 
 
 4.74 
 
 3.60 
 
 11.33 
 
 10.52 
 11.32 
 
 9.70 
 10.56 
 
 10.08 
 10.82 
 
 10.14 
 10.90 
 
 10.17 
 10.91 
 
 10.17 
 10.93 
 
 128-6 
 
 1 
 9 
 
 6.67 
 
 6.74 
 
 6.65 
 
 6.47 
 
 6.17 
 
 5.74 
 
 5.40 
 
 4.71 
 
 3.51 
 
 10.67 
 
 9.95 
 10.66 
 
 9.24 
 9.98 
 
 10.17 
 10.21 
 
 9.62 
 10.26 
 
 9.64 
 10.29 
 
 9.64 
 10.30 
 
 130-20 
 
 1 
 9 
 
 8.174 
 
 8.132 
 
 8.076 
 
 7.778 
 
 7.382 
 
 6.993 
 
 6.354 
 
 5.590 
 
 3.500 
 
 9.854 
 
 9.321 
 9.619 
 
 9.013 
 9.342 
 
 9.119 
 9.417 
 
 9.140 
 9.433 
 
 9.151 
 9.449 
 
 9.151 
 9.495 
 
 130-21 
 
 1 
 9 
 
 8.056 
 
 8.021 
 
 7.972 
 
 7.681 
 
 7.319 
 
 6.958 
 
 6.292 
 
 5.549 
 
 3.526 
 
 6.798 
 
 6.650 
 6.626 
 
 6.464 
 8.661 
 
 8.523 
 8.703 
 
 8.533 
 8.703 
 
 8.544 
 8.714 
 
 8.544 
 8.714 
 
 130-18 
 
 1 
 9 
 
 8.451 
 
 8.396 
 
 8.319 
 
 7.986 
 
 7.549 
 
 7.146 
 
 6.472 
 
 5.715 
 
 3.535 
 
 10.75 
 
 10.36 
 10.82 
 
 9.866 
 10.39 
 
 10.05 
 10.52 
 
 10.08 
 10.55 
 
 10.10 
 10.57 
 
 10.10 
 10.57 
 
 130-19 
 
 1 
 9 
 
 8.347 
 
 8.300 
 
 6.236 
 
 7.924 
 
 7.500 
 
 7.104 
 
 6.451 
 
 5.660 
 
 3.528 
 
 10.22 
 
 9.896 
 10.28 
 
 9.492 
 9.928 
 
 9.641 
 10.02 
 
 9.662 
 10.04 
 
 9.578 
 10.07 
 
 9.578 
 10.07 
 
 129-19 
 
 1 
 9 
 
 S.049 
 
 8.931 
 
 8.764 
 
 8.382 
 
 7.910 
 
 7.528 
 
 
 6.014 
 
 3.646 
 
 12.15 
 
 11.51 
 12.11 
 
 10.94 
 11.56 
 
 11.18 
 11.71 
 
 11.21 
 11.74 
 
 11.23 
 11.75 
 
 11.23 
 11.77 
 
 129-11 
 
 1 
 9 
 
 8.951 
 
 8.840 
 
 8.581 
 
 8.299 
 
 7.854 
 
 7.514 
 
 
 6.0O7 
 
 3.542 
 
 10.96 
 
 10.66 
 11.05 
 
 10.23 
 10.66 
 
 10.40 
 10.77 
 
 10.42 
 10.79 
 
 10.43 
 10.80 
 
 10.43 
 10.80 
 
 129-10 
 
 1 
 9 
 
 8.972 
 
 8.854 
 
 6.694 
 
 6.299 
 
 7.661 
 
 7.514 
 
 6.675 
 
 6.000 
 
 3.563 
 
 11.50 
 
 11.08 
 11.57 
 
 10.58 
 11.11 
 
 10.77 
 11.23 
 
 10.80 
 11.27 
 
 10.82 
 11.27 
 
 10.82 
 11.26 
 
 129-8 
 
 1 
 9 
 
 9.090 
 
 8.979 
 
 8.806 
 
 8.396 
 
 7.958 
 
 7.583 
 
 6.924 
 
 6.056 
 
 3.438 
 
 12.08 
 
 11.60 
 12.22 
 
 11.01 
 11.65 
 
 11.25 
 11.81 
 
 11.29 
 11.84 
 
 11.31 
 11.86 
 
 11.31 
 11.87 
 
 l»-9 
 
 1 
 9 
 
 9.097 
 
 8.986 
 
 8.806 
 
 8.396 
 
 7.944 
 
 7.556 
 
 6.903 
 
 6.083 
 
 3.590 
 
 12.70 
 
 12.11 
 12.81 
 
 11.42 
 12.17. 
 
 11.70 
 12.37 
 
 11.75 
 12.40 
 
 11.77 
 12.41 
 
 11.77 
 12.42 
 
 130-27 
 
 1 
 9 
 
 9.153 
 
 9.042 
 
 6.944 
 
 6.542 
 
 7.966 
 
 7.576 
 
 6.696 
 
 6.083 
 
 3.500 
 
 11.51 
 
 11.11 
 11.56 
 
 10.64 
 11.13 
 
 10.82 
 11.26 
 
 10.85 
 11.28 
 
 10.86 
 11.30 
 
 10.87 
 11.30 
 
 130-28 
 
 1 
 9 
 
 9.132 
 
 9.000 
 
 8.917 
 
 6.528 
 
 7.965 
 
 7.559 
 
 6.944 
 
 6.090 
 
 3.500 
 
 11.04 
 
 10.70 
 11.10 
 
 10.33 
 10.36 
 
 10.48 
 10.83 
 
 10.49 
 10.85 
 
 10.51 
 10.87 
 
 10.51 
 10.66 
 
 130-26 
 
 1 
 9 
 
 9.361 
 
 9.229 
 
 9.118 
 
 9.319 
 
 8.116 
 
 7.729 
 
 7.090 
 
 6.250 
 
 3.500 
 
 11.61 
 
 11.20 
 11.66 
 
 10.79 
 11.23 
 
 10.96 
 11.36 
 
 10.98 
 11.38 
 
 11.00 
 11.40 
 
 11.00 
 11.40 
 
 130-25 
 
 1 
 9 
 
 9.549 
 
 9.389 
 
 9.264 
 
 8.792 
 
 8.264 
 
 7.868 
 
 7.116 
 
 6.313 
 
 3.526 
 
 11.67 
 
 11.46 
 11.28 
 
 11.05 
 11.49 
 
 11.21 
 11.61 
 
 11.24 
 11.64 
 
 11.25 
 11.55 
 
 11.26 
 11.66 
 
 130-22 
 
 1 
 9 
 
 5.750 
 
 5.681 
 
 5.611 
 
 5.340 
 
 5.028 
 
 4.757 
 
 4.540 
 
 3.799 
 
 2.206 
 
 8.430 
 
 8.107 
 8.474 
 
 7.687 
 8.128 
 
 7.841 
 8.229 
 
 7.868 
 8.250 
 
 7.879 
 8.261 
 
 7.679 
 8.256 
 
 130-23 
 
 1 
 
 5.604 
 
 5.542 
 
 5.472 
 
 5.208 
 
 4.903 
 
 4.660 
 
 4.250 
 
 3.722 
 
 2.229 
 
 7.048 
 
 7.483 
 7.780 
 
 7.175 
 7.515 
 
 7.291 
 7.589 
 
 7.307 
 7.600 
 
 7.323 
 7.610 
 
 7.323 
 
 7.610 
 
 CONFIDENTIAL 
 
32 
 
 CONFIDENTIAL 
 
 NACA EM E54E25 
 
 •a; 
 
 K 
 
 ^ 
 
 K 
 H 
 EH 
 
 < 
 
 m 
 
 K 
 M 
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 > 
 
 
 u^ 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 CM m 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 S!3 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 I,'. 
 
 
 
 
 
 
 
 
 0» r- 
 
 M cv: 
 
 to CTi 
 
 lo in 
 
 
 
 CM ij' 
 
 to CD 
 
 
 OD <£> 
 
 ID to 
 
 
 
 
 la 
 
 
 
 
 ■* "* 
 
 in in 
 
 in in 
 
 in <o 
 
 ■* in 
 
 lO (- 
 
 
 
 
 
 
 
 
 
 
 
 
 
 J3 
 
 
 
 r-> <-! 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 r^ r^ 
 
 
 
 
 '^. 
 
 
 , 
 
 
 
 
 
 
 
 
 
 
 
 
 r- . 
 
 CO . 
 
 
 
 
 
 
 
 
 
 
 
 to 1 
 
 
 
 
 
 CO I 
 
 
 to 1 
 
 to 1 
 
 
 
 
 
 
 
 
 
 
 
 
 
 Kl 1 
 
 
 
 
 
 ^ I 
 
 
 
 
 
 (D j 
 
 « 1 
 
 (0 I 
 
 CD 1 
 
 CM 1 
 
 
 
 
 ID HI 
 
 to 1 
 
 
 tt 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 o- 
 
 a. 
 
 ^ 1 
 
 
 '-' ' 
 
 '-' ' 
 
 '-' ' 
 
 rJ t 
 
 ■^ 1 
 
 
 
 ^ 1 
 
 «-• 1 
 
 
 
 
 
 
 
 ^ 1 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 ss 
 
 
 
 
 
 ^ 
 
 
 
 
 
 
 
 
 O! (O 
 
 
 
 rO N 
 
 OD CD 
 
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 CD <~* 
 
 
 
 
 
 
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 in in 
 
 \n in 
 
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 ■* in 
 
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 r- CD 
 
 
 
 CO O 
 
 
 
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 '-' "-• 
 
 •-^ r^ 
 
 
 
 
 
 
 
 
 >-< ^ 
 
 
 
 
 
 
 
 
 
 
 
 "=. 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 r- ^ 
 
 
 
 
 
 
 
 8S! 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 t- r- 
 
 
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 (D CD 
 
 CM ■* 
 
 <M a> 
 
 CO in 
 
 
 
 
 CO O 
 
 d 
 
 ^ ^ 
 
 
 rf « 
 
 
 
 
 
 ^ in 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 O. 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 CD a> 
 
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 ^ ,-t 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
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 rJ N 
 
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 ID <n 
 
 
 
 
 
 
 
 ■* in 
 
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 m in 
 
 ■* in 
 
 
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 rJ rJ 
 
 
 
 
 
 
 
 '-' '-' 
 
 
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 s 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 M CM 
 
 r-l lO 
 
 ■* in 
 
 O CM 
 
 oj 
 
 'I' ■^1' 
 
 ^ il> 
 
 
 
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 in (O 
 
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 in (O 
 
 
 
 
 
 
 
 
 
 ■-< (M 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
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 N I 
 
 
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 ^ I 
 
 
 
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NACA EM E54E25 
 
 CONFIDENTIAL 
 
 37 
 
 CONFIDENTIAL 
 
38 
 
 CONriDEHTIAL 
 
 NACA EM E54E25 
 
 CONFIDENTIAL 
 
MCA EM E54E25 
 
 CONFIDENTIAL 
 
 39 
 
 
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40 
 
 CONFIDENTIAL 
 
 NACA EM E54E25 
 
 9 Combustion-gas static pressure 
 
 Wire-cloth or solid metal wall air-side temperature 
 
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 instrumentation on wire-cloth porous-wall afterburner. 
 
 CONFIDENTIAL 
 
MCA EM E54E25 
 
 CONFIDENTIAL 
 
 41 
 
 9 Cooling-air static pressure 
 
 Q Cooling-air total pressure 
 
 Q Cooling-air temperature 
 
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 and 
 
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42 
 
 CONFIDENTIAL 
 
 MCA EM E54E25 
 
 
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NACA EM E54E25 
 
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 43 
 
 
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 Figure 8. - Typical circumferential profiles of wire-cloth 
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 CONFIDENTIAL 
 
WACA EM E54E25 
 
 CONTIDENTIAL 
 
 45 
 
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 Figure 8. - Concluded. Typical circumferential profiles of wire-cloth 
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 CONFIDENTIAL 
 
46 
 
 CONFIDENTIAL 
 
 NACA EM E54E25 
 
 3C0C 
 
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 64 
 
 72 
 
 (a) AfterDurnlng temperature profiles. Exhaust-gas temperature, 2954° Rj total flow ratio, 
 0.0716. 
 
 Figure 9. - Typical longitudinal profiles for wire-cloth afterburner. Altitude, 35,000 
 feet; flight Mach number, 1.0. 
 
 CONFIDENTIAL 
 
MCA EM E54E25 
 
 CONFIDENTIAL 
 
 47 
 
 
 1 1 ' 
 
 
 
 
 
 
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 Statlon, in. 
 
 (b) Afterburning static-pressure and coolant-flow profiles. Exhaust-gas temperature, 
 2954° R; total flow ratio, C.0716. 
 
 Figure 9. - Continued. Typical longitudinal profiles for wire-cloth afterburner, rtltltude, 
 35,000 feet; flight Mach number, 1.0. 
 
 CONFIDENTIAL 
 
48 
 
 CONFIDENTIAL 
 
 MCA EM E54E25 
 
 
 
 
 
 
 
 
 
 
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 CONFIDENTIAL 
 
NACA RM E54E25 
 
 COKFIDENTIAL 
 
 49 
 
 
 
 
 
 
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 Station, In. 
 
 (d) Nonaftsrburning static-pressure and coolant-flow profiles. Exhaust-gas temperature, 
 1249° R; total flow ratio, C.0951. 
 
 Figure 9. - Concluded. Typical longitudinal profiles for wire-cloth afterburner. Altitude, 
 35,000 feet; flight Mach number, 1.0. 
 
 CONFIDENTIAL 
 
50 
 
 CONFIDENTIAL 
 
 WACA EM E54E25 
 
 XeuuBtjo 
 
 CONFIDENTIAL 
 
MCA EM E54E25 
 
 COKFIDEIWIAL 
 
 51 
 
 
 
 
 
 
 
 -p 
 
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52 
 
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 NACA RM E54E25 
 
 
 
 
 
 
 
 
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 5^ 
 
 CO 
 
 d a) 
 
 2 S 
 
 1 H 
 
 cd 
 
 • 4-> 
 -H O 
 rH HJ 
 
 (U 43 
 
 •Uf bs/qx 'doop aanssaad-of^B^ts aSBaaAB XBfiuajajuinojf q 
 
 CONFIDENTIAL 
 
MCA EM E54E25 
 
 CONFIDENTIAL 
 
 53 
 
 1.0 
 
 ail a 
 B-i Eh 
 
 
 -P 
 
 cd 
 u 
 
 0) 
 
 o 
 c 
 
 (U 
 
 q; 
 
 Ch 
 •H 
 
 -d 
 I 
 
 -p 
 aJ 
 ^1 
 
 EH 
 
 .3 
 
 y 
 
 
 
 
 
 \ 
 
 
 
 
 
 \ 
 
 
 
 
 
 \ 
 
 
 
 
 
 \ 
 
 
 
 
 
 \ 
 
 
 
 Series Channel 
 1 9 
 
 128 D ■ 
 
 129 O ^ 
 
 130 A ▲ 
 
 ^ 
 
 . 
 
 
 
 
 > 
 
 
 
 
 i 
 
 ^ 
 
 
 - 
 
 D .005 .010 .015 .020 .025 
 Coolant-flow ratio, (pV)^/(pU)g 
 
 (a) Reynolds number, approximately 75,000. 
 
 Figure 12. - Correlation of afterburning cooling data for 
 wire-cloth afterburner. 
 
 CONFIDENTIAL 
 
54 
 
 CONFIDENTIAL 
 
 NACA EM E54E25 
 
 1.0 
 
 EH 
 
 I 
 
 cd 
 
 EH 
 
 
 -P 
 
 Cd 
 
 u 
 
 (U 
 
 o 
 
 d 
 
 i) 
 
 u 
 
 <u • 
 
 <^l 
 
 fH 
 •H 
 
 I 
 
 -P 
 
 a) 
 ^1 
 
 (1) 
 
 EH 
 
 .06 
 
 .04 
 
 y 
 
 
 
 
 
 \ 
 
 
 
 
 
 \ 
 
 
 
 
 
 \ 
 
 
 
 
 
 \ 
 
 
 
 
 
 \ 
 
 
 
 Series Channel 
 1 9 
 
 128 D ■ 
 
 129 ♦ 
 
 130 A ▲ 
 
 ^ 
 
 ^ 
 
 
 
 
 o 
 
 
 
 
 
 
 ^ 
 
 
 
 
 
 V. 
 
 
 
 
 
 "^ 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 ♦ 
 
 
 
 
 
 
 
 .005 .010 .015 
 
 Coolant-flow ratio, (pV)£l/(pU) 
 
 .020 
 
 .025 
 
 (b) Reynolds number, approximately 300,000. 
 
 Figure 12. - Continued. Correlation of afterburning cooling 
 data for wire-cloth afterburner. 
 
 CONFIDENTIAL 
 
NACA EM E54E25 
 
 CONFIDENTIAL 
 
 55 
 
 1.0 
 
 cd 
 
 Eh 
 
 -P 
 
 cd 
 
 u 
 
 Q) 
 U 
 
 a 
 d) 
 u 
 d) 
 
 tH 
 ^M 
 •H 
 
 I 
 
 Q) 
 t-i 
 7i 
 ■P 
 
 Cd 
 u 
 
 ^ 
 dj 
 Eh 
 
 .06 
 
 
 
 1 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 Series Channel 
 1 9 
 
 128 D ■ 
 
 129 O 4 
 
 130 A A 
 
 
 \ 
 
 
 \o 
 
 > 
 
 
 
 ^ 
 
 \ 
 
 
 
 
 
 ^ ■ 
 
 
 
 
 *^t- 
 
 
 
 
 "^ 
 
 
 
 
 
 .005 .010 .015 .020 
 
 Coolant-flow ratio, (pV) /(pU) 
 
 a, £) 
 
 (c) Reynolds number, approximately 500,000. 
 
 Figure 12. - Continued. Correlation of after- 
 biirning cooling data for wire -cloth afterburner. 
 
 CONFIDENTIAL 
 
56 
 
 CONFIDENTIAL 
 
 MCA EM E54E25 
 
 1.0 
 
 E-i 
 I 
 
 I 
 
 M 
 
 -P 
 
 u 
 
 Q) 
 
 o 
 
 c 
 
 u 
 
 <D 
 <fH 
 
 •H 
 
 I 
 
 (U 
 !h 
 
 :=! 
 -p 
 cd 
 u 
 
 0) 
 
 a; 
 Eh 
 
 .oe 
 
 .04 
 
 y 
 
 
 
 
 \ 
 
 
 
 
 \ 
 
 
 
 
 \ 
 
 
 
 
 \ 
 
 
 
 
 \ 
 
 
 Series Channel 
 1 9 
 
 128 □ ■ 
 
 129 O ^ 
 
 130 A A 
 
 \ 
 
 
 
 \ o 
 
 
 
 
 
 
 
 
 
 \4 
 
 
 
 
 
 
 
 
 
 
 
 
 
 V 
 
 
 
 
 \ 
 
 
 
 
 
 .005 .010 .015 .020 
 Coolant-flow ratio, (pV)j^/(pU)g 
 
 (d) Reynolds number, approximately 800,000. 
 
 Figure 12. - Continued. Correlation of after- 
 burning cooling data for wire-cloth afterburner. 
 
 CONFIDENTIAL 
 
 I 
 
NACA EM E54E25 
 
 CONFIDENTIAL 
 
 57 
 
 1.0 
 
 Eh 
 I 
 
 tH EH 
 
 -P 
 
 U 
 
 0) 
 O 
 
 c 
 
 <D 
 fn 
 <U 
 <iH 
 <iH 
 •H 
 TJ 
 I 
 0) 
 
 u 
 :i 
 
 -p 
 cd 
 
 (U 
 
 .4 
 
 .1 
 
 .06 
 
 .04 
 
 y 
 
 
 
 
 \ 
 
 
 
 
 \ 
 
 
 
 
 \ 
 
 
 
 
 \ 
 
 
 
 
 \ 
 
 
 Series Channel 
 1 9 
 
 128 D ■ 
 
 129 O ^ 
 
 130 A A 
 
 \ 
 
 
 
 V 
 
 
 
 
 ♦ 
 
 \ 
 
 
 
 
 t 
 
 
 
 
 \ 
 
 
 
 
 
 \* 
 
 
 
 4 
 
 '\ 
 
 
 
 
 \ 
 
 
 
 
 \ 
 
 .005 .010 .015 .020 
 Coolant -flow ratio, (pV)„/(pU) 
 
 (e) Reynolds number, approximately 1,000,000. 
 
 Figure 12. - Continued. Correlation of after- 
 burning cooling data for wire-cloth afterburner. 
 
 CONFIDENTIAL 
 
58 
 
 CONFIDENTIAL 
 
 MCA EM E54E25 
 
 1.0 
 
 -p 
 
 eS 
 U 
 
 <U 
 
 V 
 
 a 
 i) 
 I-: 
 
 (U 
 
 tn 
 
 -d 
 I 
 
 -p 
 
 a 
 
 !-i 
 
 0) 
 
 i- 
 
 .06 
 
 .04 
 
 .03 
 
 .02 
 
 y 
 
 
 
 
 \ 
 
 
 
 
 \ 
 
 
 
 
 \ 
 
 
 
 
 \ 
 
 
 
 
 \ 
 
 
 Series Channel 
 1 9 
 
 128 D ■ 
 
 129 O ♦ 
 
 130 A A 
 
 \ 
 
 
 
 v^ 
 
 
 
 
 
 \° 
 
 
 
 
 N, 
 
 
 
 
 \* 
 
 
 
 
 \ 
 
 
 
 
 \ 
 
 V 
 
 
 
 
 \ 
 
 
 
 
 \ 
 
 
 
 
 \ 
 
 
 
 
 
 .005 .010 .015 .020 
 Coolant-flow ratio, (pV)^/(pU)g 
 
 (f) Reynolds number, approximately 1,500,000. 
 
 Figure 12. - Continued. Correlation of after- 
 burning cooling data for wire-cloth afterburner. 
 
 CONFIDENTIAL 
 
MCA EM E54E25 
 
 CONFIDENTIAL 
 
 59 
 
 1.0 
 
 
 li-l 
 
 cd 
 !-. 
 
 a 
 
 S 
 
 .06 
 
 .04 
 
 .03 
 
 .02 
 
 \, 
 
 
 1 
 
 
 
 \ 
 
 
 
 
 
 \ 
 
 
 
 
 
 \ 
 
 
 
 
 
 \ 
 
 
 
 
 
 \ 
 
 
 
 
 
 ^ 
 
 
 
 
 
 
 
 
 
 
 
 
 ^ 
 
 A 
 Reyn 
 
 pproximate 
 olds number, 
 Re 
 
 --. 75,000 
 
 
 
 \\ 
 
 vV 
 
 
 
 
 \n 
 
 \>. 
 
 
 
 
 V 
 
 \ 500 
 
 r300,000 
 ,000 
 
 
 
 \ 
 
 \\ 
 
 
 
 
 
 
 -300,000 
 
 
 
 
 \\ 
 
 1,000,000 
 
 
 
 
 1,500,000 
 
 
 
 
 
 
 
 .005 .010 .015 
 
 Coolant-flow ratio, (pV) /(pU) 
 
 .020 
 
 .025 
 
 (g) Mean curves for approximate Reynolds numbers of 75,000 to 
 1,500,000. 
 
 Figure 12. - Concluded. Correlation of afterburning cooling 
 data for wire-cloth afterburner. 
 
 CONFIDENTIAL 
 
60 
 
 COKFTDEmiAL 
 
 NACA EM E54E25 
 
 i CD 
 
 Eh 
 
 EH 
 
 ■P 
 U 
 V 
 
 u 
 
 B 
 
 d 
 
 0) 
 
 u 
 
 EH 
 
 .03 
 
 .02 
 
 .01 
 
 
 Coolant-flow 
 
 
 ratio. 
 
 
 (pV)a 
 
 
 (pU)g 
 
 o 
 
 0.002 
 
 a 
 
 .003 
 
 O 
 
 .0035 
 
 A 
 
 .004 
 
 V 
 
 .005 
 
 ■^ 
 
 .008 
 
 17 
 
 .0125 
 
 ^ 
 
 .0135 
 
 L 
 
 .0185 
 
 4 6 10 
 Reynolds number, Re 
 
 20 
 
 4Cxl05 
 
 Figure 13. - Variation of temperature-difference ratio with Reynolds number 
 for nonaf terburning cooling data. 
 
 CONFIDENTIAL 
 
MCA RM E54E25 
 
 COKFIDEHTIAL 
 
 61 
 
 1.0 
 
 Eh 
 I 
 
 Eh 
 
 W 
 
 -P 
 ctf 
 U 
 
 i) 
 o 
 C 
 (U 
 Jh 
 <U 
 
 <iH 
 
 tN 
 
 •H 
 
 TJ 
 
 I 
 
 ^ 
 
 -p 
 cd 
 
 !^ 
 
 1) 
 Eh 
 
 .06 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 \ 
 
 
 
 
 
 
 \ 
 
 
 
 
 \ 
 
 
 ^ 
 
 Reynolds 
 number, 
 Re 
 
 105 
 
 
 
 \ 
 
 \ 
 
 
 
 
 
 \ 
 
 
 
 
 
 \, 
 
 
 
 
 
 \ 
 
 10^ 
 
 .005 .010 .015 
 Coolant-flow ratio, (pV) /(pU) 
 
 .020 
 
 Figure 14. - Correlation of nonafterburning cooling data for 
 wire -cloth afterburner. 
 
 CONFIDEHTIAL 
 
62 
 
 COKFIDEHTIAL 
 
 MCA EM E54E25 
 
 1.0 
 
 0) 
 
 B-i 
 
 
 01 
 ■H 
 
 +-> 
 
 (tl 
 
 0) 
 
 EH 
 
 .06 
 
 .04 
 
 \ 
 
 
 
 
 
 
 \ 
 
 
 
 
 
 
 
 
 
 
 
 
 \ 
 
 
 
 
 
 
 ^k 
 
 
 
 
 
 
 \ 
 
 
 
 
 
 
 \ 
 
 V 
 
 
 
 Afterburning 
 
 Nonafterburning 
 
 
 
 \ 
 
 
 
 
 
 "" 
 
 V 
 
 \\ 
 
 "^ 
 
 Reynolds 
 
 number, 
 
 Re 
 
 105 
 ■~~-0.75xlo5 
 
 
 
 
 \ \ 
 
 V 
 
 
 
 
 
 \ 
 
 \ 
 
 
 
 
 
 
 \ \ 
 
 
 
 
 
 
 \ \ 
 
 \ \ 
 
 
 
 
 
 
 
 -10^ 
 
 
 
 
 
 v 
 
 
 
 I 
 
 .005 
 
 .010 
 
 .015 
 
 .020 
 
 .025 
 
 Coolant-flow ratio, (pV)j^/(pU)£ 
 
 Figure 15. - Comparison of cooling correlations for afterburning and 
 nonafterburning for wire-cloth afterburner. 
 
 CONFIDENTIAL 
 
MCA RM E54E25 
 
 CONFIDEHTIAL 
 
 63 
 
 (? 
 
 01 
 
 u 
 
 ■p 
 
 0) 
 V 
 
 
 
 ^^-— — 1 
 
 
 Flight Flight Altitude, Cooling -air pressure. 
 
 
 
 
 
 condition Mach ft Ib/sq In. abs 
 
 
 
 
 
 number Min. Max. 
 
 
 
 
 
 
 
 
 
 O A Sea level 25.60. 27.02 
 
 
 
 
 
 OB .8 35,000 10.85 14.55 
 O C 1.5 35,000 20.89 24.20 
 
 
 
 
 
 
 
 
 
 AD 2.0 35,000 35.04 35.70 
 
 1800 
 
 
 
 
 
 
 z 
 
 ' 
 
 
 
 
 
 
 
 
 
 
 1600 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 i 
 
 
 
 
 
 
 
 
 
 
 
 
 
 -V- 
 
 
 . Appro 
 
 ximate 
 
 peak 
 
 temper 
 
 ature 
 
 
 
 
 1400 
 
 
 
 Y 
 
 
 limit of present vrire cloth 
 
 
 
 
 
 
 
 
 due to oxidation of braze 
 
 
 
 
 
 
 
 
 
 alloy 
 
 
 
 
 1200 
 
 
 
 
 1^ 
 
 
 
 
 
 
 
 
 
 
 
 
 V^ 
 
 ^. 
 
 
 
 
 
 
 
 
 1000 
 
 
 
 
 
 \ 
 
 
 
 
 
 
 
 
 800 
 
 
 
 
 
 
 
 
 
 -O 
 
 
 
 
 .02 .04 .06 
 
 Total flow ratio, Vg^/\! 
 
 .08 
 
 .10 
 
 g 
 
 - Cooling characteristics of transpiration-cooled wire-cloth 
 uniform permeability distribution. Exhaust-gas 
 
 Figure 16 
 
 afterburner havin 
 temperature, 3700'^ R. 
 
 CONFIDEHTIAL 
 
64 
 
 CONFIDENTIAL 
 
 NACA EM E54E25 
 
 800 
 
 
 K 
 
 uo 
 
 •H 
 
 
 crt 
 
 •V 
 
 1 
 
 J1 
 
 M Eh 
 
 C 
 
 
 ■H 
 
 ». 
 
 fH 
 
 (1) 
 
 n 
 
 S-i 
 
 o 
 
 r< 
 
 C) 
 
 -u 
 
 
 !rt 
 
 ■(-> 
 
 (-, 
 
 (1) 
 
 a) 
 
 r-i 
 
 u. 
 
 d 
 
 B 
 
 M 
 
 a; 
 
 
 ■!-> 
 
 600 
 
 400 
 
 
 
 
 
 
 Transpiratlon- 
 
 
 
 texhaust-gas 
 temperature, 
 
 3700 
 3200 
 
 
 -^ 
 
 
 ■'^ 
 
 *- — ^ 
 
 afterburner 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 r orceu-cudvecuiuu- 
 cooled afterburner 
 
 
 
 
 
 
 
 
 
 
 
 
 2400 
 
 K 
 o 
 
 ^ 
 
 -p 
 a) 
 u 
 <u 
 
 ■p 
 
 r-\ 
 iH 
 0) 
 
 8 
 
 i 
 
 :! 
 
 2000 
 
 1600 
 
 1200 
 
 800 
 
 400 
 
 practical 
 cooling- 
 "air pressure' 
 
 Approximate peak temperature 
 limit for present wire cloth 
 due to oxidation of braze 
 alloy. 
 
 ■ Maximum practical 
 cooling-air pressure 
 
 Wire-cloth transpiration- 
 cooled afterburner 
 
 .04 
 
 .08 .12 .16 
 Total flow ratio, Wa/w 
 
 .20 
 
 .24 
 
 Figure 17. - Comparison of forced-convection and transpiration cooling 
 applied to same afterburner. Uniform-permeability porous wall. Flight 
 Mach number, 0.8; altitude 35,000 feet. 
 
 CONFIDENTIAL 
 
MCA EM E54E25 
 
 CONFIDENTIAL 
 
 65 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 Series Channel 
 1 9 
 
 128 □ ■ 
 
 129 O ♦ 
 
 130 A ▲ 
 
 
 
 
 
 Theoretical equations 
 
 X 
 
 H 
 o 
 
 1 
 ■=»■ 
 
 
 
 
 
 
 
 + ^ 
 0) 
 
 II 
 
 01 > 
 
 1 
 
 
 
 
 
 
 
 
 
 
 
 
 
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 1 
 
 
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 * 'oi-;bj souaaajj-tp-sanrjBasdms:^ Xboiis-iosuj, 
 
 CONFIDENTIAL 
 
66 
 
 CONFIDEHTLAL 
 
 NACA EM E54E25 
 
 
 
 
 
 
 
 tQ 
 
 a 
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 •H 
 ■P 
 
 cd 
 3 
 cr 
 
 01 
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 td 
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 a m 
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 'OT^Ba souaaajjfp-axnriBjaduia^ x^^xrjajoaqj, 
 
 CONFIDEIWIAL 
 
MCA EM E54E25 
 
 CONFIDEIWIAL 
 
 67 
 
 I 
 
 
 
 
 
 
 
 
 
 
 Eh 
 
 IB 
 
 L 
 
 
 
 
 Series Channel 
 1 9 
 
 127 O • 
 
 128 D ■ 
 
 129 O ^ 
 
 130 A A 
 
 
 
 Theoretical equation 
 
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 1 
 
 CONFIDENTIAL 
 
68 
 
 CONFIDEHTIAL 
 
 NACA EM E54E25 
 
 
 
 
 
 
 
 Theoretical equations 
 T,., - To 
 
 -. rH 
 + ■-< 
 
 r-^ 
 
 cd 
 
 u 
 
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 Series Channel 
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 127 O • 
 
 128 O ■ 
 
 129 O ♦ 
 
 130 i^ A 
 
 
 
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 CONFIDENTIAL 
 
 NACA-Lannley - 8-19-54 - 350 
 
-< '-H (1) 
 
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 ; oj CO g o 
 
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