Отрывные течения. Том 3 - Чжен П.
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Laminar Flow Over Axisymmetric Compression Surfaces; Preliminary Results
at Mach Number 6.78, US Naval Ordnance Laboratory Rept, 7402, March 1961;
NOL Preprint, Oct. 1961.
51. Beckwith I. E., Gallagher J. J., Heat Transfer and Recovery
Temperature on a Sphere with Laminar, Transitional and Turbulent Boundary
Layers at Macn Numbers of 2.00 and 4.15, NACA TN 4125, Dec 1957.
52. Francis W. L., D a v e у W. Т., Base Heating Experiments on Slender
Cones in Hypersonic Flow, IAS Paper № 62-179, presented at the IAS
National Summer Meeting, Los Angeles, California, June 1962.
53. T h о m a n n H., Measurements of Heat Transfer and Recovery
Temperature in Regions of Separated Flow at a Mach Number of 1.8,
Flygtekniska Forsokanstalten, Stockholm, Rept 82, 1959.
54. С a v e n G. R., Measurements of the Heat Transfer Coefficients on a
Forward-facing Step at a Mach Number of 1.8, Flygtekniska
Forsokanstalten, Stockholm, Rept SE, 75 : 3, 1960.
55. С h a r w a t A, F., Dewey C. F., Roos J. N., H i t z J. A., An
Investigation of Separated Flows, Part II: Flow in the Cavity and Heat
Transfer, J. Aerospace Sci., 28. № 7, 513-527 (July 1961).
56. В r i n i с h P. F., Recovery Temperature and Heat Transfer Near
Two-dimensional Roughness Elements at Mach 3.1, NACA TN 4213, 1958.
57. N a у s m i t h A., Heat Transfer and Boundary Layer Measurements in
a Region of Supersonic Flow Separation and Reattachment, Royal Aircraft
Establishment, Tech. Note Aero. 2558, May 1958.
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ГЛАВА XI
58. N а у s m i t h A., Measurements of Heat Transfer in Bubbles of
Separated Flow in Supersonic Air Streams, Royal Aircraft Establishment,
Tech. Memo Aero. 709, Feb. 1961.
59. McConnell D. G-, Free-flight Observation of a Separated Turbulent
Flow Including Heat Transfer up to Mach 8,5, NACA D-278, Oct. 1961.
60. Eckert E. R. G., Engineering Relations for Friction and Heat
Transfer to Surface in High Velocity Flow, J. Aeronaut. Sci., 22, № 8
(Aug. 1955).
61. Larson H. K., Heat Transfer in Separated Flows, J. Aerospace Sci.,
731-738 (Nov. 1959).
62. Becker J. V., Korycinski P. F., Heat Transfer and Pressure
Distribution at Mach Number of 6.8 on Bodies with Conical Flares and
Extensive Flow Separation, NACA RM L56F22, 1956.
63. Ferguson H., Schaefer J. W., Heat Transfer and Pressure Distribution
on Cone-cylinder Flare Configuration with Boundary Layer Separation, NASA
TN D-1436, 1962.
64. R о s h к о E., Simplified Method for Estimating Compressible
Laminar Heat Transfer with Pressure Gradient, NACA TN 3888, 1956.
65. R о s h к о E., Tucker, М., Approximation Calculation of the
Compressible Turbulent Boundary Layer with Heat Transfer and Arbitrary
Pressure Gradient, NACA TN 4154, 1957.
66. J а с к J. R., Wisniewski R. J., D i а с о n i s N. S., Effects of
Extensive Surface Cooling on Boundary Layer Transition, NACA TN 4094,
Oct. 1957.
67. D i а с о n i s N. S., Wisniewski R. J., Jack J. R., Heat Transfer
and Boundary Layer Transition on Two Blunt Bodies at Mach Number 3.12,
NACA TN 4099, Oct. 1957.
68. Czarnecki K. R.,Sinclair A. R., A Note on the Effect of Heat
Transfer on Peak Pressure Rise Associated with Separation of Turbulent
Boundary Layer on a Body of Revolution (NACA RM-10) at a Mach Number of
1.61, NACA TN 3997, April 1957.
69. Green L., Jr., N a 11 K. L., Experiments on Porous-wall Cooling and
Flow Separation Control in a Supersonic Nozzle, J. Aerospace Sci., 26, №
11, 689-699 (Nov. 1959).
70. В 1 о о m М. H., P a 11 о n e A., Heat Transfer to Surface in the
Neighborhood of Protuberances in Hypersonic Flows, Proc. 1957 Heat
Transfer and Fluid Mechanics Institute (held at California Institute of
Technology on June 1957), 249-278.
71. T h о m a n n H., Measurements of Heat Transfer Recovery,
Temperature and Pressure Distribution of Delta Wings at M = 3,
Flygtekniska For-sokanstalten (the Aeronautical Research Institute of
Sweden), Rept 93, Dec. 1963.
72. S t a i n b а с к P. С., Heat-transfer Measurements at a Mach Number
of 4.95 on Two 60° Swept Delta Wings with Blunt Leading Edges and
Dihedral Angles of 0° and 45°, NASA TN 549, 1961.
73. Gunn C. G., Heat-transfer Measurements on the Apexes of Two 60°
Sweptback Delta Wings (Panel Semiapex Angle of 30°) having 0° and 45°
Dihedral at a Mach Number of 4.95, NASA TN 550, 1961.
74. O'N eal R. L., Bond >. C., Heat Transfer to 0° and 75° Swept Blunt
Leading Edges in Free Flight at Mach Numbers from 1.90 to 3.07, NASA TN
D-1256, 1962.
75. S t a 1 d e r J. R., Nielsen H. V., Heat Transfer from a Hemisphere
Cylihder Equipped with Flow-separation Spikes, NACA TN 3287, Sept. 1954.
76. Eggers A. J., Hermach C. A., Initial Experiments on the Aerodynamic
Cooling Associated with Large-scale Vortical Motions in Supersonic Flow,
NACA RMA54L13, March 1955.
77. В о g d о n о f f S. M-, Vas I. E., Preliminary Investigation of
Spiked Bodies at Hypersonic Speeds, J. Aerospace Sci. (Feb. 1959); Heat
