Разномодульная теория упругости - Амбарцумян С.А.
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сверхзвуковой скоростью. Доклады АН СССР. 1947, т. LV11I, № 4 (см. также
раздел "Нестационарные течения:").
Краснлыцикова Е. А., Влияние вихревой пелены при установившемся движении
крыла со сверхзвуковой скоростью. Доклады, 1947, АН СССР, т. LVII1, № 6.
Фалькович С. В., О подъемной силе крыла конечного размаха в сверхзвуковом
потоке, ПММ, 1947, т. XI, вып. 1, стр. 171-176.
Фалькович С. В., К теории крыла конечного размаха в сверхзвуковом потоке,
ПММ, 1947, т. XI, вып. 3, стр. 391-394.
Нелинейные задачи Метод годографа
Walchner О., Zur Frage der Widerslandaverringerung von Trag-fliigeln bei
Clberschallgeschwindigkeit durch Doppeldeckeranord-nung,
Luftfahrtforschung, vol. 14, pp. 55-62, 1937.
T а у 1 о r G. I. and Maccoll J. W., The Air Pressure on a Cone Moving at
High Speeds, Proc. Roy. Soc. (A)., vol. 139,
pp. 278-293, 1933.
С г о с с о L., Singolarita della currente gassosa iperacustica nell
intomo di una prora a diedro, L'Aerotecnica, vol. 17,
pp. 519-534, 1937.
Maccoll J. W., The Conical Shock Wave Formed by a Cone
Moving at High Speed, Proc. Roy. Soc. of London (A)"
vol. 159, pp. 459-472, 1937.
Perri Antonio, Completed Tabulation in the USA of Tests of 24 Airfoils at
High Mach Numbers, NACA, L-143, 1946.
Ferri Antonio, Supersonic Tunnel Tests of Projectiles in
Germany and Italy, NACA, L-152, 1946.
L i g h t h i 11 M. J., A Note on Supersonic Biplanes, R 8" M,
No. 2002, October 1944.
Lighthill M. J., Two-Dimensional Supersonic Airfoil Theory, R. 8s M, No.
1929, January 1944.
Hankins G. A., Experiments on Reynolds Number Effect on Projectiles at
Supersonic Speeds, NPL Eng. Div., 221/46.
Maccoll J. W., Investigations of Compressible Flow at Sonic
Speeds, Sixth International Congress for Applied Mechanics,
1946, Paris.
88
СВЕРХЗВУКОВАЯ АЭРОДИНАМИКА
Р а с к D. С., On the Properties of Supersonic Two-Dimensional Free Gas
Jets and the Calculation of the Shock Waves Which Oceur, Sixth
International Congress for Applied Mechanics, 1946, Paris.
W e i b u 11 W., Ondes planes de pression auz fronts descontinus, Sixth
International Congress for Applied Mechanics, 1946, Paris.
Ackeret J., Shock Waves and the Mechanism of Compressibility Drag, Sixth
International Congress for Applied Mechanics, 1946, Paris.
Liepmann H. W., The Interaction Between Boundary Layer and Shock Waves in
Transonic Flow, Journal of the Aeronautical Sciences, vol. 13, No. 12,
pp. 623-637, December 1946.
Kaplan C., Effect of Compressibility at High Subsonic Velocities on the
Lifting Force Acting on an Elliptic Cylinder, NACA T. N., No. 1118, July
1946.
Wright H. and Donaldson C., Comparison of Two-Dimensional Air Flows 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 T. N., No. 10SS,
1946.
Emmons H. W., The Theoretical Flow of a Frictionless. Adiabatic, Perfect
Gas Inside of a Two-Dimensional Hyperbolic Nozzle, NACA T. N.. No. 1003,
1936.
T s i e n H. S. and F e j e г A., A Method for Predicting the Transonic
Flow over Airfoils and Similar Bodies from Data Obtained at Small Mach
Numbers, GALCIT Report, December 31, 1944.
Davies D. М., Shock Waves in Compressible Flow; An Outline of the
Phenomena Occurring in the Trans sonic Speed Range, Aircraft Eng., pp.
261-263, August 1946.
В e a v a n J. A. and Hyde G. A. М., Compressibility Increase of Lift and
Moment on EC 1250 for Low-Speed CL 0.17, R & M, No. 2055, 14 p.
September, 1942.
E g g i n k, A Study of Compression Shocks with Boundary Layer
Separation, AAF. Translation No. 1126. 18 p., December 1946.
Kaplan Carl, The Flow of a Compressible Fluid Past a Curved Surface, NACA
and R 8s R., No. 3K02, 1943.
Kaplan Carl., The Flow of a Compressible Fluid Past a Circular Arc
Profile, NACA, L-216, 69 p., October, 1944.
ЛИТЕРАТУРА
89
Lindsey W. F., Effect of Compressibility on the Pressures and Forces
Acting on a Modified NACA 65/ 3-019 Airfoil Having a
0.20-Chord Flap. NACA, L-76, January 1946.
Pearson E. O. et al, Effects of Coomprescibility on the Maximum Lift
Characteristics and Spanwise Load Distribution of a 12-Foot Span Fighter-
Type Wing of NACA-230 Series Airfoil Section, NACA, L-51, Novermber 1945.
G о t h e r t B., Plane and Three-Dimensional Flow at High Subsonic
Speeds, NACA Т. М., No. 1105, October 1946.
Beavan J. A. and Hyde G. A. М., Examples of Pressure Distributions at
Compressibility Speeds on EC 1250, R 8s M, No. 2056, September 1942.
Ackeret J., Feldman F. and Rо11 N.. Investigations of Compression Shocks
and Boundary Layers in Gases Moving at High Speed (Mitteilungen aus dem
Institut fur Aerodynamik an der ETH in Zurich, No. 10), January 1947,
NACA Т. М., No. 1113, January 1947.
Wicselberger C., Ober den Einfliiss der Windkanalbegrenzung auf den
Wiederstand insbesondere im Bereich der kompressib-len Stromung,
Luftfahrtforschung, Bd. 19, стр. 124-128, May 6, 1942.
Byrne Robert W., Experimental Constriction Effects in High-Speed Wind
