Отрывные течения. Том 2 - Чжен П.
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International Congress in the Aeronautical Science, Stockholm, Aug. 1962.
45. Fottinger H., Mitt. Verein. Grosskesselbesitzer, 73 (1939).
46. M a i r W. A., Experiments on Separation of Boundary Layers on Probes
in Front of Blunt-nosed Bodies in a Supersonic Air Stream, Phil. Mag.,
43, seventh.series, (July 1952).
47. N e i с e S. E., Experimental Investigation of the Aerodynamic
Characteristics of a Ballistic-type Missile, NACA RM A54CQ4, April 1954.
48. H u n t G. K., Supersonic Wind-tunnel Study of Reducing the Drag of a
Bluff Body at Incidence by Means of a Spike, Royal Aircraft
Establishment, Rept Aero. 2606, May 1958.
49. M о e с k e 1 W. E., Flow Separation Ahead of Blunt Bodies at
Supersonic Speeds, NACA TN 2418, July 1951.
50. Gorges H. A., Some Tests on the Formation of Conical Flows due to
Separation, Tech. Note HSA 50, Weapons Research Establishment, Australian
Defence Scientific Service, South Australia, April 1959.
51. Album H. H., Spiked Blunt Bodies in a Supersonic Flow, Air Force
Office of Scientific Research, Washington 25, DC, Rept AFOSR 307,
. June 1961.
52. Daniels L. E., Yoshi har a H., Effects of the Upstream Influences of
a Shock Wave at Supersonic Speeds in the Presence of a Separated Boundary
Layer, WADC Tech. Rept 54-31, Jan. 1954.
53. S t a 1 d e r J. R., Nielsen N. V., Heat Transfer from a Hemisphere
Cylinder Equipped with Flow-separation Spikes, NACA TN 3287, Sept.
54. В о g d о n о f f S. М., V a s I. E., Preliminary Investigations of
Spiked Bodies at Hypersonic Speeds, J. Aerospace Sci., 26, N4 2, 65-74
(Feb. 1959).
55. Bernstein H., Brunk W. E., Exploratory Investigation of Flow in the
Separated Region Ahead of Two Blunt Bodies at Mach Number 2, NACA RM
E55D07B, June 1955.
56. Maull D. J., Hypersonic Flow over Axially Symmetric Spiked Bodies, J.
Fluid Mech., 8, Part 4, 584-592 (Aug. i960).
ОТРЫВ ПОТОКА С ПЕРЕДНЕЙ КРОМКИ
27"
57. К о р а 1 Z., Tables of Supersonic Flow Around Cones, Massachusetts
Institute of Technology, 1947.
58. С r a w f о r d D. H., Investigation of the Flow over a Spiked-nose
Hemi-sphere-cylinder at a Mach Number of 6,8; NASA TN D-118, Dec. 1959.
59. Wood C. J., A Study of Hypersonic Separated Flow, Ph. D. thesis,
University of London, Oct. 1961 (available as DDC AD 401652).
60. Liepmann H. ff., Roshko A., D h a w a n S., On Reflection of Shock
Waves from Boundary Layers, NACA TN 2334, 1951.
61. E g g e г s A. I., H e г m a с h C. A., Initial Experiments on the
Aerodynamic Cooling Associated with Large-scale Vortical Motions in
Supersonic Flow, NACA RM A54L13, March 1955.
62. Bestall D., Turner J., The Effect of a Spike Protruding in Front of a
Bluff Body at Supersonic Speeds, ARC Tech. Rept R & M 3007, Jan 1952.
63. Jones J. J., Flow Separation from Rods Ahead of Blunt Noses at Mach
Number 2.72; NACA RM L52E05a, July 1952.
64. von Karman Th., The Problem of Resistance in Compressible Fluids,
GALCIT Pub. № 75, 1936 from Atti Roy. Accad. Ital., Cl. Sci. Fis. Mat. e
Nat., 14 (1936).
БИБЛИОГРАФИЯ
Black J.,Hunt R. D., Some Measurements of Leading-edge Separation Bubbles
on a 10 percent Thick Symmetrical Aerofoil, J. Roy. Aeronaut. Soc., 819-
823 (Dec. 1953).
Brown С. E-, Michael W. H., On Slender Delta Wings With Leading-edge
Separation, NACA TN 3430, April 1955.
Cole J. D., В г a i n e r d J. J., Slender Wings at High Angles of Attack
in Hypersonic Flow, American Rocket Society, Air Force Office of
Scientific Research, International Hypersonics Conference, MIT, Aug.
1961.
Crabtree L. F., Effects of Leading-edge Separation on Thin Wings in Two-
dimensional Incompressible Flow, J. Aeronaut. Sci., 21, № 8, 597-604
(Aug. 1957).
E 11 e B. J., J о n e s J. P., A Note on the Vorticity Distribution on
the Surface of Slender Delta Wings with Leading-edge Separation, J. Roy.
Aeronaut. Soc., 195-198 (March 1961).
Hahn M. S., Pressure Distribution and Mass Injection Effects in the
Transitional Separated Flow over a Spiked Body at Supersonic Speed, J.
Fluid Mech., 24, Part 2, 209-223 (1966).
Maull D. J., Hypersonic Flow Over Axially Symmetric Spiked Bodies, J.
Fluid Mech., 8, 584 (1960).
Reinecke W. G., Album H. H., J ohani Т., Pitot and Static Pressure
Measurements in the Separated Region of Spiked Cylinder in Hypersonic
Flow, Aerospace Research Labs., Office of Aerospace Research, ARL 65-237,
Nov. 1965.
Sacks A. H., Nielsen J. H., Goodwin F. K., A Theory for the Low-speed
Aerodynamics of Straight and Swept Wings With Flow Separation, Vidya,
Research and Development, Rept № 9, March 31, 1963.
Sharp A. W., The Supersonic Flow Past a Leading-edge Separation Bubble,
J. of Fluid Mech., 5, 445 (1959).
Ward J. W., The Behaviour and Effects of Laminar Separation Bubbles on
Aerofoils in Incompressible Flow, J. Roy. Aeronaut. Soc., 783 (Dec.
1963).
ОГЛАВЛЕНИЕ
Основные обозначения .
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Глава VII. Характеристики отрывных течений ......................... 7
