Abstract
With reduction of the density in a hypersonic stream the transition of the flow from continuum to free molecule takes place gradually. The transition region may be divided into several regimes, in each of which a definite physical phenomenon is most significant. For the case of the flow in the vicinity of the forward stagnation point of a blunt body these phenomena include increase of the thickness of the detached shock wave and of the boundary layer, the presence of viscous flow in the entire disturbed layer ahead of the blunt body, reduction of the number of collisions between molecules and the associated relaxation effects, the increasing role of the interaction of the stream molecules with the surface, and the phenomena of slip and temperature jump.
This is a preview of subscription content, log in via an institution to check access.
Similar content being viewed by others
References
F. Robben and L. Talbot, “Measurement of shock wave thickness by the electron beam fluorescence method”, Phys. Fluids, vol. 9, no. 4, 633, 1966. 1966.
A. B. Ivanov, “Shock wave structure in air for Mach numbers from 2. 6 to 6”, Izv. AN SSSR, MZhG [Fluid Dynamics], no. 2, 152, 1967.
A. V. Ivanov, “Experimental study of the effect of Mach and Reynolds numbers on the structure of supersonic rarefied gas flow in the vicinity of the forward stagnation point of a blunt body”, Izv. AN SSSR, MZhG [Fluid Dynamics], no. 3, 1967.
V. S. Avduevskii, “Approximate method for calculating three-dimensional laminar boundary layer flow”, Izv. AN SSSR, OTN, Mekhanika i mashinostroenie, no. 2, 1962.
M. N. Kogan, Rarefied Gasdynamics [in Russian] Moscow, Izd-vo Nauka, 1967.
W. D. Hayes and R. F. Probstein, Hypersonic Flow Theory [Russian translation], Moscow, Izd-vo inostr. lit., 1962.
M. C. Adams and R. F. Probstein, “On the validity of continuum theory for satellite and hypersonic flight problems at high altitudes”, Jet Propulsion, vol. 28, 1958.
Ho Hung-Ta and R. F. Probstein, “The compressible viscous layer in rarefied hypersonic flow”, in: Rarefied Gas Dynamics, Supple. 1, New York-London, Acad. Press., 1961.
Yu. N. Belyaev and V. B. Leonas, “Kinetic coefficients of molecular oxygen and nitrogen at high temperatures”, Teplofizika vysokikh temperatur, no. 5, 732, 1966.
H. M. Mott-Smith, “The solution of the Boltzman equation for a shock wave”, Phys. Rev., vol. 82, 885, 1951.
V. S. Galkin, “On the limits of applicability of continuum mechanics for describing the flow in the vicinity of the stagnation point at high supersonic speeds”, Tr. TsAGI, no. 764, 1959.
M. Van Dyke, “Theory of the compressible boundary layer in the second approximation with application to hypersonic flow past blunt bodies”, collection: Hypersonic Flow Research [Russian translation], edited by F. R. Riddell, Moscow, Izd-vo Mir, 1964.
V. P. Stulov and G. F. Telenin, “Nonequilibrium supersonic air flow past a sphere”, Izv. AN SSSR, Mekhanika, no. 1, 3, 1965.
J. A. Fay and F. R. Riddell, “Theory of stagnation-point heat transfer in dissociated air”, JAS, vol. 25, no. 2, 73, 1958.
C. B. Cohen and E. Reshotko, “The compressible laminar boundary layer with heat transfer and arbitrary pressure gradient”, NACA Rep., no. 1294, 1956.
R. S. Hickman and W. H. Giedt, “Heat transfer to a hemisphere-cylinder at low Reynolds numbers”, AIAA Journal, vol. 1, no. 3, 154, 1963.
Author information
Authors and Affiliations
Rights and permissions
About this article
Cite this article
Avduevskii, V.S., Ivanov, A.V. Rarefied gas flow near the forward stagnation point of a blunt body at hypersonic speeds. Fluid Dyn 3, 17–22 (1968). https://doi.org/10.1007/BF01019892
Issue Date:
DOI: https://doi.org/10.1007/BF01019892