Hypersonic Viscous Shock Layer Calculation of Leeward Vortex-Induced Heat Transfer on a Sharp Cone at a High Angle of Attack

[+] Author and Article Information
J. C. Adams

Project Support and Special Studies Section, Aerodynamics Projects Branch, von Kármán Gas Dynamics Facility, ARO, Inc., AEDC Division, A Sverdrup Corporation Co., Arnold Air Force Station, Tenn.

J. Heat Transfer 99(2), 307-313 (May 01, 1977) (7 pages) doi:10.1115/1.3450686 History: Received February 24, 1977; Online August 11, 2010


An analysis technique applicable to the problem of leeward vortex-induced heat transfer on a sharp cone at high angles of incidence under hypersonic laminar flow conditions is presented. The analysis, a three-dimensional hypersonic viscous shock layer approach in conjunction with a numerical solution procedure, is shown to be both applicable and accurate based on comparisons of heat-transfer distributions, surface pressure distributions, and leeward meridian flow-field profile measurements taken in a hypersonic wind tunnel. Detailed calculations of the embedded vortex flow field on the leeward side of the cone are presented in such a manner as to clearly portray exactly how embedded vortex flow influences local heating rates.

Copyright © 1977 by ASME
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