1. MARSCHAK, T. A., The Role of Project Histories in. the Study of R&D. RAND P-2850, Jan. 1964.
2. BECKER, JOHN V., A Hindsight Study of the NASA Hypersonic Research Engine Project. Study for NASA/OAST Propulsion Div., 1976. Unpublished.
3. ROBINS, BENJAMIN, Resistance of the Air and Experiments Relating to Air Resistance. Philosophical Transactions, London, 1946-47.
4. LYNAM, E. J. H., Preliminary Report of Experiments on a High-Tip-Speed Airscrew at Zero Advance. British ACA, R&M No. 596, Mar. 1919.
5. RAYLEIGH, LDRD, On the Flow of Compressible Fluid Past an Obstacle. Papers, Vol. 6 (1916). See also Vol. 5.
6. CALDWELL, F. W., and FALES, E. N., Wind Tunnel Studies in Aerodynamic Phenomena at High Speeds. NACA Report No. 83, 1920.
7. HUNSAKER, J. C., Forty Years of Aeronautical Research. Smithsonian Institution, Publication 4237, Washington, 1956.
8. REED, S. A., Air Reactions to Objects Moving at Rates Above the Velocity of Sound, with Application to the Air Propeller. NACA TM 168, Nov. 1922.
9. Douglas, G. P., and Wood, R. McK., The Effects of Tip Speed on Airscrew Performance. An Experimental Investigation of an Airscrew Over a Range of Speeds of Revolution from "Model" Speeds up to Tip Speeds in Excess of the Velocity of Sound in Air. British ARC, R&M No. 884, June 1923.
10. STACK, JOHN, Remarks Made at AIAA History Committee Session, AIAA Summer Meeting, 1965 (Tape transcription obtained from RAND Corp.).
11. BRIGGS, L. J., and DRYDEN, H. L., Aerodynamic Characteristics of Airfoils at High Speeds. NACA Report No. 207, 1925.
12. DRYDEN, H. L., The Next Fifty Years. Aero Digest, July 1953, p. 158.
13. BRIGGS, L. J., and DRYDEN, H. L., Pressure Distribution Over Airfoils at High Speeds. NACA Report No. 255, 1927.
14. FARREN, W. S., The Aerodynamic Art. 44th Wilbur Wright Lecture. Jour. of the Royal Aeronautical Society, Vol. 60, July 1956.
15. BRIGGS, L. J., and DRYDEN, H. L., Aerodynamic Characteristics of 24 Airfoils at High Speeds. NACA Report No. 319, 1929.
16. BRIGGS, L. J., and DRYDEN, H. L., Aerodynamic Characteristics of Circular Arc Airfoils at High Speeds, NACA Report No. 365, 1931.
17. JACOBS, E. N., and SHOEMAKER, J. M., Tests on Thrust Augmentors for Jet Propulsion. NACA TN 431, Sept. 1932.
18. JACOBS, E. N., Methods Employed in America for the Experimental Investigation of Aerodynamic Phenomena at High Speeds. Volta Meeting Paper, Sept. 30-Oct. 6, 1935. NACA Misc. Paper No. 42, Mar. 1936.
19. Interview, E. N. JACOBS, Mar. 9, 1978.
20. STACK, J., Compressible Flows in Aeronautics. 8th Wright Brothers Lecture, Journal Aero. Sciences, Vol. 12, No. 2, Apr. 1945; see also comment by Dr. H. L. Dryden, p. 145.
21. HUGUENARD, E., High-Speed Wind Tunnels, NACA TM No. 318, 1925. (Translation, La Technique Aeronautica, Dec. 1924.)
22. Interview with I. H. ABBOTT, Mar. 8, 1978.
23. Interviews with W. F. LINDSEY, several dates, Jan.-Mar. 1978.
24. STANTON, T. E., High-Speed Wind Channel for Tests on Airfoils. British ARC, R&M No. 1130, 1928.
25. STACK, J., The NACA High-Speed Wind Tunnel and Tests of Six Propeller Sections. NACA Rept. No. 463, 1933.
26. STACK, JOHN, and VON DOENHOFF, A. E., Tests of 16 Related Airfoils at High Speed. NACA Rept. No. 492,1934.
27. STACK, JOHN, The Compressibility Burble. NACA TN 543, Oct. 1935.
28. STACK, J., LINDSEY, W. F., and LITTELL, R. E., The Compressibility Burble and the Effect of Compressibility on the Pressures and Forces Acting on an Airfoil. NACA Rept. 646, 1938.
29. JONES, R. T., Recollections from an Earlier Period of American Aeronautics. Am. Rev. of Fluid Mech., Vol. 9, 1977.
30. 8-ft High Speed Tunnel Log Book No. 1. Files of Transonic Aerodynamics Branch, Langley Research Center, NASA.
31. BECKER, J. V., and LEONARD, L. H., High-Speed Tests of a Model Low-Wing Transport Airplane. NACA Report 742, 1942.
32. ROBINSON, R. G., and WRIGHT, R. H., Estimation of Critical Speeds of Airfoils and Streamline Bodies. NACA Wartime Report No. L-781, 1940.
33. ABBOTT, I. H., and VON DOENHOFF, A. E., Summary of Airfoil Data. NACA Report 824, 1945.
34. STACK, J., Tests of Airfoils Designed to Delay the Compressibility Burble. NACA TR 763, 1943, and NACA TR 976, 1944.
35. LINDSEY, W. F., et al., Aerodynamic Characteristics of 24 NACA 16-Series Airfoils at Mach Numbers Between 0.3 and 0.8. NACA TN 1546, 1948.
36. LADSON, C. L., Chordwise Pressure Distributions over Several NACA 16-Series Airfoils at Transonic Mach Numbers up to 1.25. NASA Memo. Report 6-1-59L, 1959.
37. VON DOENHOFF, A. E., et at., Low Speed Tests of Five NACA 66-Series Airfoils Having Mean Lines Designed for High Critical Mach Numbers. NACA TN 1276, 1947.
38. LOFTIN, L. K., JR., Exploratory Investigation at High and Low Subsonic Mach Numbers of Two Experimental 6-Percent-Thick Airfoil Sections Designed to Have High Maximum Lift Coefficients. NACA RM L511706. Dec. 14, 1951.
39. LEWIS, G. W., Report on Trip to Germany and Russia. Sept., Oct., 1936. 13, Nat'l. Historical Archives.
40. ABBOTT, 1. H., Review and Commentary of A. L. Levine Thesis, Apr. 1964. (Available in NASA History Office Files. See also Levine, A. L., United States Aeronautical Research Policy, 1915-1958: A Study of the Major Policy Decisions of the NACA. Ph.D. Thesis, Columbia Univ., 1963).
41. SCHLAIFER, R., Development of Aircraft Engines. Graduate School of Business Administration, Harvard Univ., Boston, 1950.
42. Interviews with M. C. ELLIS, JR., Aug. 1978.
43. MILLER, R., and SAWFRS, D., The Technical Development of Modern Aviation. Praeger Publishers, New York, 1970.
44. RUBERT, K. F., An Analysis of Jet-Propulsion Systems Making Direct Use of the Working Substance of a Thermodynamic Cycle. NACA WR L-714, Feb.1945.
45. FERRI, A., Completed Tabulation in the U.S. of Tests of 24 Airfoils at High Mach Numbers. NACA WR No. L-143,1945.
46. WIESELBERGER, C., On the Influence of the Wind Tunnel Boundary on the Drag, Particularly in the Region of Compressible Flow. Luftfahrt Forschung 19, 1942.
47. GILRUTH, R. R., Resume and Analysis of NACA Wing-Flow Tests. Anglo American Aeronautical Conference, Sept. 1947.
48. GOETHERT, B., Druckverteilungs und Impulverlustschaubilder fur das Profit NACA 0006, 0009, 0012, 0015, 0018 bei hohen Unterschaligeschwindigkeiten, FB Nr. 1505/1, 2, 3, 4, 5, DVL, 1941.
49. HABEL, L. W., Transonic Tunnel progress report. Memo. for Langley Files, Apr. 28, 1947.
50. BECKER, J. V., Transonic Aerodynamics. Chapter prepared in 1949 for proposed Aeronautical Engineering Handbook, A. Klemin, editor. (Unpublished; handbook never completed due to Dr. Klernin's death.)
51. Minutes of Meeting of Langley General Aerodynamics Committee, Jan. 16,1948. W. J. Underwood, Sec'y. Available in Central Files, LRC.
52. BECKER, J. V., Characteristics of Airfoils at Transonic Speeds. Unclassified paper given at NACA-University Conference at Langley Laboratory, June 1948.
53. DONALDSON, C. DUP., and WRIGHT, R. H., Comparison of 2-dimensional Air Flows about an NACA 0012 Airfoil of 1-inch Chord at Zero Lift in Open and Closed 3-inch Jets and Corrections for Jet-Boundary Interference. NACA TN 1055, May 1946.
54. STACK, J., Methods for Investigation of Flows at Transonic Speeds. NOL Aeroballistics Res. Facilities Dedication Symposium. June 27-July 1, 1949. See also an updated version presented at the 3rd International Aero Conference, London, Sept. 7-11, 1951.
55. DALEY, B. N., and DICK, R. S., Effect of Thickness, Camber and Thickness Distribution on Airfoil Characteristics at Mach Numbers up to 1.0. NACA TN 3607, 1958.
56. DALEY, B. N., and HABEL, L. W., Preliminary Investigation of Airfoil Characteristics Near M-1. NACA Conf. on Aerodynamic Problems of Transonic Airplane Design. Sept. 27-29, 1949.
57. GUDERLEY, G. K., Singularities at the Sonic Velocity. AF-WADC-FTR- 1171- ND., June 1948.
58. GUDERLEY, G. K., and YOSHIHARA, H., The Flow Over a Wedge Profile at Mach Number 1. Jour. Aero. Sci., Vol. 17, No. 11, 1950.
59. BECKER, J. V., Proposal to Include Guderley Airfoils in Langley Research Programs. Memo for Chief of Research, Mar. 11, 1949.
60. SINNOTT, C. S., On the Flow of a Sonic Stream Past an Airfoil Surface. Jour. Aero. Sci., Vol. 26, 1959.
61. VON KARMAN, T., Compressibility Effects in Aerodynamics. Jour. Aero. Sci., Vol. 8, July 1941.
62. BUSEMANN, A., A Review of Analytical Methods for the Treatment of Flows with Detached Shocks. NACA TN 1858, April 1949.
63. VINCENTI, W. G., and WAGONER, C. B., Transonic Flow Past a Wedge Profile with Detached Bow Wave. NACA Rept. 1095, 1952.
64. GRAHAM, D. J., The Development of Cambered Airfoil Sections Having Favorable Lift Characteristics at Supercritical Mach Numbers. NACA TN 1771, 1948.
65. GRAHAM, D. J., NITZBERG, G. E., and OLSON, R. N., A Systematic Investigation of Pressure Distributions at High Speeds Over Five Representative NACA Low-drag and Conventional Airfoil Sections. NACA Rept. 832, 1945.
66. GOETHERT, B., Hockgeschwindigkeits messungen an Profilen gleicher Dickenverteilung mit verschiedenen Krummung in DVL-Hockgeschwindigkeits Wind Kanal (2.7 m), FB Nr. 1910/6 DVL, 1944.
67. PEARCEY, H. H., The Aerodynamic Design of Section Shapes for Swept Wings. Vol. 3, Advances in the Aeronautical Sciences, Pergamon Press, 1962.
68. WOERSCHINC;, T. B., Negative Camber Airfoils for Transonic Flight. Jour. Aero. Sci., Vol. 18, No. 6, 1951.
69. HILTON, W. F., Use of Negative Camber in the Transonic Speed Range. British ARC, R&M MO, 1953.
70. Advanced Technology Airfoil Research Conference. NASA Langley Research Center, Mar. 7-9, 1978.
71. POLLOCK, N., Two Dimensional Airfoils at Transonic Speeds. Australian Dept. of Supply, Aero. Res. Labs. Note 314, 1969.
72. WHITCOMB Interview, March 29, 1978.
73. LACHMAN, G. V., Aspects of Design of Low-Drag Aircraft. Vol. 2, Boundary Layer Flow Control. Pergamon Press, 1961.
74. WHITCOMB, R. T., Review of NASA Supercritical Airfoils. Paper No. 74-10 presented at 9th Congress of the ICAS, Haifa, Israel, Aug. 1974.
75. LOLFTIN, Interview, Apr. 5, 1978.
76. MURMAN, E. M., and COLE, J. D., Calculation of Plane Steady Transonic Flows. AIA Jour., Vol. 9, No. 1, 197 1.
77. GARADEDIAN, P. R., and KORN, D. G., Analysis of Transonic Airfoils. Common Pure and Applied Math., Vol. 24, 1971.
78. Daily Press, Newport News, Va., Dec. 18, 1952.
79. LIEPMANN, H. W., and PUCKETT, A. E., Aerodynamics of a Compressible Fluid. John Wiley & Sons, New York, 1947.
80. STODOLA, A., Steam and Gas Turbines. McGraw-Hill, New York, 1927.
81. Minutes of Langley General Aerodynamics Committee, Meeting of July 25, 1947. (Available in Langley central files.)
82. GLAUERT, H., Wind Tunnel Interference on Wings, Bodies, and Airscrews. British ARC, R.&M. No. 1566,1933.
83. GOLDSTEIN, S., and YOUNG, A. 0., The Linear Perturbation Theory of Compressible Flow with Application to Wind Tunnel Interference. British ARC 6865, Aero. 2262FM601, 1943.
84. ALLEN, H. J., and VINCENTI, W. G., Wall Interference in a Two-Dimensional-Flow Wind Tunnel with Consideration of the Effect of Compressibility. NACA Rept. 782, 1944.
85. BECKER, J. V., High-Speed Wind-Tunnel Tests of the NACA 23012 and 23012-64 Airfoils. NACA ACR, Feb. 1941. (Also WR L-357)
86, ORLIN, W. J., Application of the Analogy Between Water Flow with a Free Surface and 2-Dimensional Compressible Gas Flow. NACA Report No. 875,1947. (See also NACA RM No. L8FI7, 1948.)
87. BYRNE, R. W., Experimental Constriction Effects in High-Speed Wind Tunnels. NACA ACR L41,07a, May 1944. (Also WR L-74)
88. ABBOTT, 1. H., and THOMPSON, F. L., Material Presented at Seminar on High-Speed Aerodynamics. Wright Field, Sept. 6, 1945. (Unpublished NACA document.)
89. WHITCOMB, R. T., An Investigation of a Typical High-Speed Bomber Wing Speed Tunnel. 1. Basic Wing Characteristics. NACA in the Langley 8-foot High-NACA RM No.L5FO9, Army Air Forces,1945.
90. WHITCOMB, R. T., An Investigation of the Effects of Sweep on the Character- istics of a High-Aspect-Ratio Wing in the Langley 8-Foot High-Speed Tunnel. NACA RM No. L6J0Ia, 1946.
91. WRIGHT, JOHN B., and LOVING, DONALD L., High-Speed Wind-Tunnel Tests of a 1/16-Scale Model of the D-558-1 Research Airplane. NACA RM No. L6J09, 1946.
92. MATTSON, A. T., Force and Longitudinal Control Characteristics of a 1/16-Scale Model of the Bell XS-1 Transonic Research Airplane at High Mach I k, Numbers. NACA RM No. L7AO3, 1947.
93. RITCHIE, V. S., et al., An 8-Foot Axisymmetrical Fixed Nozzle for Subsonic Mach Numbers up to 0.99 and for a Supersonic Mach Number of 1.20. NACA RM L5OAO3a, 1950.
94. GOETHERT, B. H., Transonic Wind Tunnel Testing. Pergamon Press, New York, 1961.
95. BECKER, J. V., Preliminary Investigation of a Flapped Airfoil at a Mach Number of 1.6. NACA Conference on Supersonic Aerodynamics, June 19, 1947.
96. CORSON, B. W., JR., Memo for Chief, Compressibility Research Division, Oct. 16, 1943.
97. BECKER, J. V., Pressure Distribution Measurements on the Rotating Blades of a Single-Stage axial-Flow Compressor. Proceedings, Compressor Conference, NACA AERL, Cleveland, Ohio, Sept. 11, 1946. (See also NACA TN 1189 by Runckel and Davey, Feb., 1947.)
98. DAVEY, R. S., Multiple-Pressure Transfer Device. Instruments, Vol. 23, No. 4, Apr. 1950.
99. HABEL, L. W., The Langley Annular Transonic Tunnel and Preliminary Tests of an NACA 6&-006 Airfoil. NACA RM No. LB-A23, June 1948.
100. HABEL, L. W., HENDERSON, J. H., and MILLER, M. F., The Langley Annular Transonic Tunnel. NACA TR 1106, 1952.
101. STACK, J., and DALEY, B. N., Comparison of Pressure Distribution Measurements for an NACA 230-Series Airfoil from Flight and Wind-Tunnel Tests at High Mach Numbers. NACA ACR, Mar. 11, 1943.
102. WEAVER, J. H., A Method of Wind-Tunnel Testing Through the Transonic Range. Jour. Aero. Sci., Vol. 15, No. 1, Jan. 1948.
103. HARTMAN, E. P., Adventures in Research. NASA SP-4302, 1970.
104. POLHAMUS, E., et al., Summary of Results Obtained by Transonic Bump Method on Effects of Platform and Thickness on the Characteristics of Wings at Transonic Speeds. NACA TN 3469, 1955.
105. GOETHERT, B., and KOLB, A., Drop Tests to Determine the Drag of Model SC-50 at High Velocities. DVL, Berlin, Tech. Rept. Z, WB-11-252, 1944.
106. Thompson, F. L., Flight Research at Transonic and Supersonic Speeds with Free-Falling and Rocket-Propelled Models. 2nd International Aero. Conference, New York, May 1949.
107. BECKER, J. V., Conference at Wright Field on March 15, 1945, to discuss transonic airplane proposed by Bell Aircraft Corp. Memo. for Chief of Research, Mar. 21, 1945.
108. COUCH, L. M., and BROOKS, C. W., JR., Effect of Blockage Ratio on Drag and Pressure Distributions for Bodies of Revolution at Transonic Speeds.NASA TN D-7331, 1973.
109. SHORTAL, J. A., A New Dimension. Wallops Island Flight Test Range: The First Fifteen Years. NASA RP 1028, Dec. 1978.
110. SOULE, H. A., Interview with W. H. Bonney on Mar. 28, 1973, NASA historical files.
111. PERRY, R. L., The Antecedents of the X-1. Paper No. P-3154, The Rand Corp., July 1965.
112. HALLION, R. P., Supersonic Flight. The MacMillan Co., 1972. PW
113. DRALEY, E. C., Origin of X-1 Airplane. Memo for J. F. Victory, Sept. 28, 1948.
114. DAVIDSON, M., Memo for Chief of Research (containing suggested specifications for a transonic research airplane), Mar. 3, 1945.
115. ELLIS, M. C., JR., and BROWN, C. E., Analysis of Supersonic Ram-jet Performance and Wind-Tunnel Tests of a Possible Supersonic Ram-jet Airplane Model. NACA ACR L5112, Dec. 1945.
116. KELLER, M. D., A History of the Langley Laboratory, 1917-1947. Comment Draft of document prepared under NASA Contract NSR-03-M2-123, Mar. 1968.
117. Interview with R. H. Wright, July 31, 1978.
118. WRIGHT, R. H., and WARD, V. G., NACA Transonic Wind-Tunnel Test Sections. NACA RM L8J06, 1948. (Also NACA Report 1231, 1955)
119. DAVIS, D. D., and MOORE, D., Analytical Study of Blockage and Lift-Interference Corrections for Slotted Tunnels Obtained by Substitution of an Equivalent Homogeneous Boundary for the Discrete Slots. NACA RM L53EO7b,1953.
120. CORSON, B. W., JR., Description and justification for Slotted Test Section, Material prepared for FY 1949 Budget, Jan. 10, 1948.
121. BECKER, J. V., Conference with Full-Scale Research Division Regarding Mach Number Control in Transonic Wind Tunnels. Memo for CRD Files, Sept. 3, 1947.
122. BECKER, J. V., Proposed Use of Ram-jet Power for Supersonic Wind Tunnels. Memo for Acting Director of Aeronautical Research (J. W. Crowley), Aug. 9, 1946.
123. BECKER, J. V., Proposed Test Section Design for Repowered 16-Foot Tunnel. Memo for Chief of Research, Jan. 2, 1948.
124. OSBORNE, R. S., High-Speed Wind-Tunnel Investigation of a 1/16-Scale Model of the D-558-2 Research Airplane at High Subsonic Mach Numbers and at Mach 1.2. NACA RM No. L9C04, Apr. 1949.
125. TURNER, L. I., JR., Program for Investigation of Slotted Test Section in Induction Aerodynamics Laboratory Facilities. Memo for CRD Files, Apr. 8, 1948.
126. NELSON, W. J., and BLOETSCHER, F., Preliminary Investigation of a Variable Mach Number Two-Dimensional Supersonic Tunnel of Fixed Geometry. NACA RM L9D29a, 1949.
127. WARD, V. G., et al., An NACA Transonic Test Section with Tapered Slots Tested at Mach Numbers to 1.26. NACA RM L5B14, 1950.
128. WRIGHT, R. H., RITCHIE, V. S., and PEARSON, A. O., Characteristics of the Langley 8-Foot Transonic Tunnel with Slotted Test Section. NACA Report 1389, 1958.
129. STACK, J., and MATTSON, A. T., Transonic Wind-Tunnel Development and Langley Aeronautical Laboratory of the NACA. Paper presented Operation at the L.A.S. Summer Meeting, 1954.
130. MATHEWS, C. W., Theoretical Study of the Tunnel-Boundary Lift Interference Due to Slotted Walls in the Presence of a Trailing Vortex System of a Lifting Model. NACA RM L53A26, 1953.
131. MAEDER, P. F., Theoretical Investigation of Subsonic Wall Interference in Rectangular Slotted Test Sections. Brown Univ., WT-6, 1951, and WT-11, 1953.
132. GOODMAN, T. R., The Porous-Wall Tunnel, Part III, Reflection and Absorption of Shock Waves at Supersonic Speeds. Cornell Aero Lab. Report No. AD-706-A-1, Nov. 1950.
133. Fortieth Annual Report of the NACA, 1954.
134. WHITCOMB interview with Walter Bonney, Mar. 27, 1973. NASA Historical Files.
135. RUNCKEL interview, July 1978.
136. STACK, J., et al., Investigation of the NACA 4- (3) (08) -030 and 4- (3) (08) -045 2-Bladed Propellers at Forward Mach Numbers to 0.725 to Determine the Effects of Compressibility and Solidity on Performance, NACA Report 999, p.1930. (Originally NACA ACR 4A10 and 4B16, 1944.)
137. COOPER, M., Comparison Tests of the 4-Foot Propeller Dynamometer in the Langley 8-Foot and 16-Foot High-Speed Tunnels. NACA CR L5H31, Mar. 1946.
138. DELANO, J. B., The Effect of High Solidity on Propeller Characteristics at High Forward Speeds from Wind Tunnel Tests of the NACA 4-(3) (06.3)-06 and -09 Two-Blade Propellers. NACA RM L6LI9, Feb. 1947.
139. DELANO, J. B., and CARMEL, M. M., Effect of Shank Design on Propeller Performance at High Speeds. NACA RM L61323, June 1946.
140. DELANO, J. B., and CARMEL, M. M., Tests of Two-Blade Propellers in the Langley 8-Foot High-Speed tunnel to Determine the Effects on Propeller Performance of a Modification of Inboard Pitch Distribution. NACA ACR L4L20,1944. Also NACA TN 2288,1951.
141. DELANO, J. B., Investigation of 2-Blade Propellers at High Forward Speeds. III. Effects of Camber and Compressibility. NACA 4-(5) (08)-03 and 4-(10)(08)-03 Blades. NACA ACR L5F15, 1945.
142. DRALEY, E. C., Propellers at High Speeds. NACA Conference on Aerodynamic Problems of Transonic Airplane Design. Ames Aeronautical Laboratory, Moffett Field, Calif., Nov. 5, 6, 1947.
143. CORSON, B. W., JR., and MAYNARD, J. D., The Langley 2000 hp Dynamometer and Tests at High Speeds of an NACA 10- (3) (08) -03 Two-Blade Propeller. NACA RM 1,7L29, and NACA TN 2859,1952.
144. MAYNARD, J. D., and SALTERS, L. B., JR., Aerodynamic Characteristics at High Speeds of Related Full-Scale Propellers Having Different Blade Section Cambers. NACA RM L8E06,1948, and NACA Report 1309.
145. MAYNARD, J. D., and STEINBERG, S., The Effect of Blade Section Thickness Ratios on the Aerodynamic Characteristics of Related Full-Scale Propellers at Mach Numbers up to 0.65. NACA RM L9D29, 1949.
146. MAYNARD, J. D., and SALTERS, L. B., JR., Aerodynamic Characteristics at High Speeds of Related Full Scale Propellers Having Different Blade-Section Cambers. NACA RM L8EO6,1948.
147. BECKER, J. V., High-Speed Pressure Distribution Investigation of Full-Scale Propeller. Memo for Chief of Research, Sept. 9, 1944.
148. EVANS, A. J., and LINER, G., Preliminary Investigation to Determine Propeller Section Characteristics By Measuring Pressure Distribution on an NACA 10-(3) (08)-03 Propeller Under Operating Conditions. NACA RM L8BI 1, July 14, 1948.
149. MAYNARD, J. D., and MURPHY, M. P., Pressure Distributions on the Blade Sections of the NACA 10-(3) (066) -033 Propeller Under Operating Conditions, NACA RM 1,91,12, Jan. 1950. (See also RM 1,91,23.)
150. GILMAN, J., JR., CRIGLER, J. L., and McLEAN, F. E., Analytical Investigation of Propeller Efficiency at Flight Speeds Near Mach Number Unity. NACA RM L905a, Feb. 1950.
151. SALTERS, L. B., JR., Correlation of One-Blade and Two-Blade Propeller Data. Memo for Files, May 4, 1950.
152. GRAY, W. H., and ALLIS, A, E., The Torsional Deflections of Several Propellers Under Operating Conditions, NACA RM L51A19, June 1951.
153. VON KARMAN, T., Where We Stand. Report of Army Air Forces Scientific Advisory Group, Aug. 1945.
154. EVANS, A. J., and LINER, G., A Wind Tunnel Investigation of the Aero dynamic Characteristics of a Full-Scale Sweptback Propeller and Two Related Straight Propellers. NACA RM L50J05, Jan. 1951.
155. DRALEY, E. C., et al., Trends in the Design and Performance of High-Speed Propellers. NACA Conference on Aerodynamics Problems of Transonic Airplane Design Langley Aeronautical Laboratory, Sept.27-29,1949.
156. DELANO, J. B., and CARMEL, M. M., Investigation of the NACA 4-(5) (08)-03 2- Blade Propeller at Forward Mach Numbers to Mach 0,925. NACA RM L9G06a, 1949.
157. WOOD, J. H., and SWIHART, J. M., The Effect of Blade Section Camber on the Static Characteristics of Three NACA Propellers. NACA RM 1,511,28, 1952.
158. MAYNARD, J. D., et al., Effect of Blade Section Camber on Aerodynamic Characteristics of Full-Scale Supersonic Type Propellers at Mach Numbers up to 1.04. NACA RM 1,56E10, 1956.
159. RIBNER, H. S., A Transonic Propeller of Delta Planform. NACA TN 1303, 1947.
160. VOGELEY, A. W., Climb and High-Speed Tests of a Curtiss No. 714-IC2-12 Four-Blade Propeller on a Republic P-47C Airplane. NACA ACR L4L07 (WR L177), Dec. 1944.
161. HAMMACK, J. B., Flight Investigation in Climb and High Speed of a Two-Blade and Three-Blade Propeller. NACA TN 1784, 1949.
162. HAMMACK, J. B., and O'BRYAN, T. C., Effect of Advance Ratio on Flight Performance of a Modified Supersonic Propeller. NACA TN 4389, 1958.
163.- GRAY, G. W., Frontiers of Flight. Alfred A. Knopf, New York, 1948.
164. ANONYMOUS, The Cooling of Air-cooled Engines by Forced Circulation of Air. "Les Ailes," Sept. 9, 11926. NACA TM No. 385, 1927.
165. Research Authorizations No. 172, June 30, 1926, and 215, June 22, 1927, LRC files.
166. WEICK, F. E., Drag and Cooling with Various Forms of Cowling for a "Whirlwind" Radial Air-Cooled Engine. NACA TN 301, 302, Oct. 1928; NACA TR 313, 314, 1929.
167. BEISEL, R., et al., The Cowling and Cooling of Radial Air-Cooled Engines. SAE Journal, Vol. 34, No. 5, May 1934.
168. SCHEY, O. W., JOHNSON, E., and GOUGH, M. N., Comparative Performance of XF7C-1 Airplane Using Several Different Engine Cowlings. NACA TN 334, 1930.
169. SCHEY, 0. W., and BIERMANN, A. E., Heat Dissipation from a Finned Cylinder at Different Fin/Airstream Angles. NACA TN 329, 1932.
170. BREVOORT, M. J., and ROLLIN, V. G., Air Flow Around Finned Cylinders. NACA Rept. 555, 1936.
171. BREVOORT, M. J., Energy Loss, Velocity Distribution, and Temperature Dis- tribution for a Baffled Cylinder Model. NACA TN 620, 1937.
172. BREVOORT, M. J., et al., Cooling Tests of a Single-Row Radial Engine with Several NACA Cowlings. NACA Rept. 596,1937.
173. PYE, D. R., The Theory and Practice of Air Cooling. Aircraft Engineering. Feb- April 1932.
174. THEODORSEN, TH., et al., Full Scale Tests of NACA Cowlings. NACA Rept. 592, 1937. See also Rept. 662, 1939.
175. ROBINSON, R. G., and BECKER, J. V., High-Speed Tests of Radial-Engine Cowlings. NACA ACR, 1939. Also NACA Rept. 745, 1942.
176. ROCALLO, F. M., Internal Flow Systems for Aircraft. NACA Rept. 713, 1941.
177. ROKUS, F., and TROLLER, TH., Tests on Ventilation Openings for Aircraft. I.A.S. Journal, Vol. 3, No. 6, Apr. 1936.
178. SILVERSTEIN, A., and BECKER, J. V., Determination of Boundary-Layer Transition on Three Symmetrical Airfoils in the Full-Scale Tunnel. NACA Rept. 637, 1939.
179. BECKER, J. V., Wind-Tunnel Investigation of Air Inlet and Outlet Openings on a Streamlined Body. NACA ACR, Nov. 1940; WRL-300, Jan. 1947; and TR 1038, 1951.
180. BECKER, J. V., and BAALS, D. D., Wind-Tunnel Tests of a Submerged-Engine "Nor," Fuselage Design. NACA ACR, Oct. 1940.
181. BIERMANN, D., and VALENTINE, E. F., Preliminary Tests of Nose- and Side Entrance Blower Cooling Systems for Radial Engines. NACA ACR, July 20, 4-1939.
182. McHUGH, J. G., Progress Report on Cowlings for Air-Cooled Engines Investigated in the 19-Foot Pressure Tunnel. NACA ARR, Aug. 8, 1941.
183. BECKER, J. V., and MATTSON, A. T., The Effect of Spinner/Body Gap on the Pressures Available for Cooling in the NACA E-Type Cowling. NACA-CB, Mar. 1943. (Also WR-497.)
184. BAALS, D. D., SMITH, N. F., and WRIGHT, J. B., The Development and Application of High-Critical-Speed Nose Inlets. NACA Rept. 920, 1948 (supersedes NACA ACR L5F30a).
185. PENDLEY, R. E., and ROBINSON, H. L., An Investigation of Several NACA 1-Series Nose Inlets at High-Subsonic Mach Numbers and at Mach 1.2. NACA RM L91,23a, 1950. See also NASA TM X-2917, 1974.
186. RE, R. J., An Investigation of Several NACA I-Series Axisymmetric Inlets at Mach Numbers from 0.4 to 1.29. NASA TM X-2917, Mar. 1974.
187. BECKER, J. V., and BAALS, D. D., The Aerodynamic Effects of Heat and Compressibility in Internal Flow Systems, and High-Speed Tests of a Ram-jet System. NACA Rept. 773, 1943. (Supersedes NACA ACR of Sept. 1942).
188. BREVOORT, M. J., et al., The Effect of Altitude on Cooling. ARR Mar. 1943. See also WRL-386.
189. BECKER, J. V., and BAALS, D. D., Simple Curves for Determining the Effects of Compressibility on the Pressure Drop Through Radiators. NACAACR L4123, Sept. 1944. (See also WRL-6.)
190. HABEL, L. W., and GALLAGHER, J. J., Tests to Determine the Effect of Heat on the Pressure Drop Through Radiator Tubes. NACA TN 1362, 1947. (See also NACA RM L8FI8,1948.)
191. FOA, J. V., and RUDINGER, G., C)n the Addition of Heat to a Gas Flowing in a Pipe at SubsonicSpeeds.Jour.Aero.Sci.,Vol.16, No.2,Feb.1949.
192. MEREDITH, F. W., Note on the Cooling of Aircraft Engines with Special Reference to Radiators Enclosed in Ducts. British ARC, R&M No. 1683, 1936.
193. WILLIAM, D. T., The Reaction jet as a Means of Propulsion at High Speeds. NACA ACR June 1941, also WR E-78.
194. AVERY, W. H., Twenty-five Years of Ramjet Development, Jet Propulsion. Vol. 25, No. 11, Nov. 1955.