Shock detachment and drag in hypersonic flow over wedges and circular cylinders
- Creators
-
Hornung, H. G.
Abstract
In a recent publication, Hornung et al. (J. Fluid Mech., vol. 871, 2019, pp. 1097–1116) showed that the shock wave stand-off distance and the drag coefficient of a cone in the inviscid hypersonic flow of a perfect gas can be expressed as the product of a function of the inverse normal-shock density ratio ε and a function of the cone-angle parameter η, thus reducing the number of independent parameters from three (Mach number, specific heat ratio and angle) to two. Analytical forms of the functions were obtained by performing a large number of Euler computations. In this article, the same approach is applied to a symmetrical flow over a wedge. It is shown that the same simplification applies and corresponding analytical forms of the functions are obtained. The functions of ε are compared with the newly determined corresponding functions for flow over a circular cylinder.
Additional Information
© The Author(s), 2021. Published by Cambridge University Press. Received 15 December 2020; revised 9 February 2021; accepted 23 February 2021. Published online by Cambridge University Press: 25 March 2021. This work was funded by the US Air Force Office of Scientific Research, contract no. FA9550-19-1-0219, PI J.M. Austin, Contract Officer I.A. Leyva. The author reports no conflict of interest.Attached Files
Submitted - 1906.06604.pdf
Files
| Name | Size | Download all |
|---|---|---|
|
md5:a4659120e2e69b1fc330c4e2e4f622c6
|
6.1 MB | Preview Download |
Additional details
- Alternative title
- Hypersonic flow over a wedge in the detached shock range
- Eprint ID
- 98787
- Resolver ID
- CaltechAUTHORS:20190923-091328424
- Air Force Office of Scientific Research (AFOSR)
- FA9550-19-1-0219
- Created
-
2019-09-23Created from EPrint's datestamp field
- Updated
-
2021-06-07Created from EPrint's last_modified field
- Caltech groups
- GALCIT