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Hypersonic flow over a wedge in the detached shock range

Hornung, H. G. (2019) Hypersonic flow over a wedge in the detached shock range. . (Unpublished)

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In a recent publication Hornung (2019) showed that the shock wave stand-off distance and the drag coefficient of a cone in inviscid hypersonic flow of a perfect gas can be expressed as the product of a function of the inverse normal-shock density ratio and a function of a cone-angle parameter, thus reducing the number of independent parameters from three (Mach number, specific heat ratio and angle) to two. By making a large number of Euler computations, analytic forms of the functions were obtained. In this article the same approach is applied to the symmetrical flow over a wedge. It turns out that the same simplification applies and corresponding analytical forms of the functions are obtained. The functions of the normal-shock density ratio are compared with newly determined corresponding functions for flow over a circular cylinder.

Item Type:Report or Paper (Discussion Paper)
Related URLs:
URLURL TypeDescription Paper
Hornung, H. G.0000-0002-4903-8419
Additional Information:This work was funded by AFOSR FA9550-19-1-0219, PI: J. M. Austin, Contract Officer: I. A. Leyva.
Funding AgencyGrant Number
Air Force Office of Scientific Research (AFOSR)FA9550-19-1-0219
Record Number:CaltechAUTHORS:20190923-091328424
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Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:98787
Deposited By: Tony Diaz
Deposited On:23 Sep 2019 16:39
Last Modified:03 Oct 2019 21:44

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