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Отрывные течения. Том 1 - Чжен П.

Чжен П. Отрывные течения. Том 1 — М.: Мир, 1972. — 300 c.
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47. С о h e n С. B., R e s h о t к о E., Similar Solutions for the
Compressible Laminar Boundary Layer with Heat Transfer and Pressure
Gradient, NACA Rept 1293, 1956.
48. Tani I., On the Approximate Solution of the Laminar Boundary Layer
Equations, J. Aerospace Sci., 21, № 7, pp. 487-504 (July 1954).
49. Lees L., Reeves B. L., Some Remarks on Integral Moment Methods for
Laminar Boundary Layers with Application to Separation and Reattachment,
GALCIT Rept № 1, Dec. 1961, AFOSR Rept № 1920; см. также Л n з, Рнв з,
Сверхзвуковые отрывные и присоединяющиеся течения, ч. 1, Общая теория и
применение ее для анализа взаимодействия скачка уилотенения с
адиабатическим пограничным слоем, Ракетная техника и космонавтика, JY" И
(1964).
50. Savage S. G. В., The Effect of Heat Transfer on Separation of Laminar
Compressible Boundary Layers, GALCIT, Separated Flows Research Project,
Rept № 2, June 1962.
51. Th waites B., Approximate Calculation of the Laminar Boundary Layer,
Aero Quart., 1, pp. 245--280 (Nov. 1949).
ДОПОЛНИТЕЛЬНАЯ ЛИТЕРАТУРА
Аренс, Отрыв потока в профилированных соплах вследствие перерасши-реппя,
Ракетная техника и космонавтика, № 8 (1963).
Аренс, Спигяер, Отрыв потока в перерасширепных ракетных соплах с
коническим сверхзвуковым участком при взаимодействии скачка уплотнения с
пограничным слоем, Ракетная техника и космонавтика, № 3 (1963).
В а г t г D. R., An Approximate Solution of Compressible Turbulent
Boundary-layer Development And Convective Heat Transfer in Convergent-
Divergent Nozzles, the American Society of Mechanical Engineers, N. Y.,
Paper 54-A-153, Nov. 28-Dec. 3, 1954.
Bogdonoff S. М., Kepler С. E., Separation of a Supersonic Turbulent
Boundary Layer, J. Aeronaut. Sci., 22, № 6 (June 1955).
Brinich P. F., Blunt Body Separation at Supersonic Speeds., /. Aeronaut.
Sci.. 25, № 5 (May 1959).
Cheng S. I., Laminar Separated Flow Within Rejoining or Reattaching
Boundary Layers, Avco Corp., Research and Advanced Development Division,
Wilmington, Mass., Tech. Memo. RAD-TM-64-66, 27 Nov. 1964.
ОТРЫВ ПОТОКА ГАЗА
291
Donaldson J.C., Myers A. W., Investigation of the Separation and
Reattachment of Flow Downstream of Two-dimensional and Rearward-facing
Steps at Mach Numbers 2, 5, 3, 5 and 5, von Karmen Gas Dynamics Facility,
Arnold Engineering Development Center, Arnold Air Force Station Tenn.,
AEDC-TR-66-106, May 1966.
Erdos J., Pallone A., Shock-Roundary Layer Interaction and Flow
Separation, AVCO Technical Rept RAD-TR-61-23, 15 Aug. 1961.
Fox J., Surface Pressure and Turbulent Air Flow in Transverse Rectangular
Notches, NASA TN D-2501, 1964.
Gillette W. B., Separation Measurements of Supersonic Turbulent Boundary
Layers Over Compression Corners, Defense Research Lab., the University of
Texas, Austin, Texas, DRL-543, 21 July 1966.
G i n о u x J. J., Laminar Separation in Supersonic and Hypersonic Flows,
von Karman Institute for Fluid Dynamics, Belgium, Final Rept, Contract AF
EOAR 65-11, 1 Nov. 1964 to 31 Oct. 1965.
Ginoux J. J., Laminar Separation in Supersonic and Hypersonic Flow, von
Karman Institute for Fluid Dynamics, Rhode-Saint-Genese, Belgium, 1 Oct.
1965 to 30 Sept. 1966, Final Rept, AFOSR 67-0615, 30 Sept. 1966.
Graham W. J., V a s I. E., An Experimental Investigation of the
Separation of a Hypersonic Boundary Layer of a Flat Plate. Part 1:
Pressure Distribution and Optical Studies at M = 11,7, Aeronaut. Res.
Labs., ARL 63-74, May 1963.
G u m a n W. J., On the Plateau and Peak Pressure of Regions of Pure
Laminar and Fully Turbulent Separation in Two-dimensional Supersonic
Flow, J. AerolSpace Sci., p. 56 (Jan. 1959).
Holden M. S., An Analytical Study of Separated Flows Induced By Shock
Wave-Boundary Laver Interaction, Cornell Aeronautical Laboratory, Inc.,
CAL Rept № A1-1972-A-3, Dec. 1965.
Holden М., Separated Flow Studies At Hypersonic Speeds. Part I: Separated
Flows over Axisymmetric Spiked Bodies, Cornell Aeronautical Laboratory,
Contract № Nonr 2653(00), Dec. 1964.
Holden М., Separated Flow Studies at Hypersonic Speeds. Part II: Two-
dimensional Wedge Separated Flow Studies, Contract № Nonr 2653(00),
Cornell Aeronautical Laboratory, CAL Rept № AF-1285-A-13(2), Dec. 1964.
Holder D. W., The Interaction between Shock Waves and Boundary Layers,
Presented at the Fifth International Aeronautical Conference, June 20-24,
1955, Preprint № 550.
Kaufman L. G., Ill, Pressure Measurements for Mach Five Flows over a
Blunt Pyramidal Configuration with Aerodynamic Controls: Part of an
Investigation of Hypersonic Flow Separation and Control Characteristics,
Air Force Flight Dynamics Lab., Research and Technology Div., Tech.
Documentary Rept № RTD-TDR-63-4239, Jan. 1964.
Nielsen J. N., Lynes L. L., Goodwin F. K., Calculation of Laminar
Separation With Free Interaction by the Method of Integral Relations,
Part I: Two Dimensional Supersonic Adiabatic Flow, AFFDL-TR-65-107, Oct.
1965.
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