Viscous shock layer flow in the windward plane of cones at angle of attack-Reference-Cited by-同舟云学术

Viscous shock layer flow in the windward plane of cones at angle of attack

Published:1973-01-10 Issue: Volume: Page:
ISSN:
Container-title:11th Aerospace Sciences Meeting
language:
Short-container-title:

Author:

EATON R.¹,KAESTNER P.¹

Affiliation:

1. Sandia Laboratories, Albuquerque, N. Mex.

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.1973-134

Reference12 articles.

1. Hypersonic boundary layer studies on a spinning sharp cone at angle of attack

2. Fliigge-Lotz,I. and Blottner, F. G. "Computation of the Compressible Laminar Boundary-Layer Flow Including Displacement Thickness Interaction Using Finite-Difference Methods,'' Stanford University, Division of Engineering Mechanics, Technical Report No. 131, 1962.

3. Lcompared with inviscid cone solutions. Figure 8 also shows that the shocks calculated for the viscous flow have a standoff di 8tance approximately equal to the inviscid st.mdoff distance plus the . ''Chemically Reacting Viscous Flow Program For Multi-Component Gas Mixtures," Sandia Corporation, SC-RR-70-754, December, 1971

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1. Calculation of the flow field past spherically blunted cones near the plane of symmetry for various shock layer flow regimes with insufflation of gas from the surface;Journal of Applied Mechanics and Technical Physics;1992

2. Three-dimensional thin viscous shock layer in the absence of planes of symmetry in the flow;Fluid Dynamics;1989

3. Hypersonic Three-Dimensional Viscous Shock-Layer Flows over Blunt Bodies;AIAA Journal;1978-12

4. Heat- and mass-transfer effects on three-dimensional hypersonic viscous shock-layer flows;2nd Thermophysics and Heat Transfer Conference;1978-05-24

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