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The hypersonic viscous effect on a flat plate with finite leading edge

Published online by Cambridge University Press:  28 March 2006

Andrew G. Hammitt
Andrew G. Hammitt
Affiliation:
Princeton University, Princeton, New Jersey
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Abstract

A method has been developed for calculating the viscous effects of the hypersonic flow on the fore part of various bodies. This method takes into account the finite leading-edge thickness of the body and the detached shock wave. The calculated pressure distributions agree with all experimental results for both air and helium over a wide range of Mach numbers and Reynolds numbers. The calculation predicts skin frictions of the order of twice those predicted by ordinary boundary-layer theory.

Information

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 5 , Issue 2 , February 1959 , pp. 242 - 256
Copyright
© 1959 Cambridge University Press

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References

Becker, J. V. 1950 Results in recent hypersonic and unsteady flow research at the Langley Aeronautical Laboratory. J. Appl. Phys. 21, 622.Google Scholar
Bertram, M. H. 1952 An approximate method of determining the displacement effects and viscous drag of laminar boudary layers in two-dimensional hypersonic flow. Nat. Adv. Comm. Aero., Wash., Tech. Note, no. 2773.Google Scholar
Bertram, M. H. 1954 Viscous and leading edge thickness effects on the pressures on the surface of a flat plate in hypersonic flows. J. Aero. Sci. 21, 430.Google Scholar
Bogdonoff, S. M. & Hammitt, A. G. 1954 The Princeton helium hypersonic tunnel and preliminary results above M = 11. Princeton University Aero. Eng. Rep. no. 260. (Also published as WADC TR 54-124).Google Scholar
Bogdonoff, S. M. & Hammitt, A. G. 1956 Fluid dynamic effects at speeds from M = 11 to 15. J. Aero. Sci. 23, 108.Google Scholar
Chang, H. K. & Pallone, A. J. 1956 Inviscid leading edge effect in hypersonic flow. J. aero. Sci. 23, 700.Google Scholar
Hammitt, A. G. & Bogdonoff, S. M. 1956 Hypersonic studies of the leading edge effect in the flow over a flat plate. J. Amer. Rocket Soc. 26, 241.Google Scholar
Hammitt, A. G. Vas, I. E. & Bogdonoff, S. M. 1956 Leading edge effect on the flow over a flat plate. at hypersonic speeds. Princeton University Aero. Eng. Rep. no. 326. (Also published as WADC TN 55-537).Google Scholar
Kendall, J. M. 1957 An experimental investigation of leading edge shock wave boundary layer interaction at M = 5·8. J. Aero. Sci. 24, 47.Google Scholar
Kuo, Y. H. 1953 On the flow of an incompressible viscous fluid past a flat plate at moderate Reynolds numbers. J. Math. Phys. 32, 83.Google Scholar
Lees, L. 1952 On the boundary layer equations in hypersonic flow and their approximate solutions. Princeton University Aero. Eng. Rep. no. 212.Google Scholar
Lees, L. 1954a Hypersonic viscous flow over an inclined wedge. J. Aero. Sci. 20, 794.Google Scholar
Lees, L. 1954b Hypersonic influence of the leading edge shock wave on the laminar boundary-layer at hypersonic speeds, GALCIT TR, no. 1.Google Scholar
Lees, L. & Kubota, T. 1956 Inviscid hypersonic flow over blunt-nosed slender bodies. J. Aero. Sci. 123, 195.Google Scholar
Lees, L. & Probstein, R. F. 1952 Hypersonic viscous flow over a flat plate. Princeton University Aero. Eng. Rep. no. 195.Google Scholar
Li, Ting-Yi & Nagamatsu, H. 1953 Shock wave effects on the laminar skin friction of an insulated flat plate at hypersonic speeds. J. Aero. Sci. 20, 345.Google Scholar
Li, Ting-Yi & Nagamatsu, H. 1955 Hypersonic viscous flow on a non-insulated flat plate. GALCIT Report, no. 25.Google Scholar
Morduchow, M. & Clarke, Joseph H. 1952 Method for calculation of compressible laminar boundary-layer characteristics in axial pressure gradient with zero heat transfer. Nat. Adv. Comm. Aero., Wash., Tech. Note, no. 2784.Google Scholar
Pai, Shih-I 1953 On strong interaction for the hypersonic boundary layer on inclined wedge. J. Aero. Sci. 20, 796.Google Scholar
Shen, S. F. 1952 An estimate of viscosity effect in hypersonic flow over an insulated wedge. J. Math. Phys. 31, 192.Google Scholar
Van Driest, E. F. 1952 Investigation of laminar boundary layer in compressible fluids using the Croco method. Nat. Adv. Comm. Aero., Wash., Tech. Note, no. 2597.Google Scholar
Vas, I. E. 1957 An experimental investigation of the pressure on a thin flat plate at hypersonic speeds. Princeton University Aero. Eng. Rep. no. 377. (Also published as WADC TN 57-104.)Google Scholar