The numerical and experimental simulation of hypervelocity flow around the HYFLEX vehicle forebody

Johnston, IA, Tuttle, SL, Jacobs, PA and Shimoda, T (1999) The numerical and experimental simulation of hypervelocity flow around the HYFLEX vehicle forebody. Shock Waves, 9 1: 57-67. doi:10.1007/s001930050139


Author Johnston, IA
Tuttle, SL
Jacobs, PA
Shimoda, T
Title The numerical and experimental simulation of hypervelocity flow around the HYFLEX vehicle forebody
Journal name Shock Waves   Check publisher's open access policy
ISSN 0938-1287
Publication date 1999-01-01
Sub-type Article (original research)
DOI 10.1007/s001930050139
Volume 9
Issue 1
Start page 57
End page 67
Total pages 11
Place of publication New York
Publisher Springer-Verlag
Language eng
Subject C1
290299 Aerospace Engineering not elsewhere classified
690302 Space transport
Abstract Numerical and experimental techniques are used to model the flow and pressure distribution around the forebody of the HYFLEX hypersonic flight vehicle. We compare numerical simulation results with modified Newtonian theory and flight data to determine the accuracy of the computational fluid dynamics (CFD) technique used. The numerical simulations closely match the trends in flight data, and show that real gas effects have a small but significant influence on the nose pressure distribution. We also present pressure results from a scale-model tested in a shock tunnel, and compare them with simulation results. For the shock tunnel experiment, the model was placed such that part of the upper surface was in a region of the test flow where nonuniformities were significant, and it was shown that the numerical simulation could adequately capture these experimental flow features. The binary scaling parameter (describing the similarity in species dissociation between flight and model) was used to design the scale-model tests in the shock tunnel, and its effectiveness is discussed. We find that matching the flight Mach number in the shock tunnel experiment is not critical for reproducing flight pressure data, so long as flight velocity is matched, and binary scaling is maintained.
Keyword Mechanics
Computational Fluid Dynamics
Shock Tunnel
Blunt Body
Hypersonic Flow
Re-entry Vehicle
Q-Index Code C1

Document type: Journal Article
Sub-type: Article (original research)
Collection: School of Mechanical & Mining Engineering Publications
 
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Created: Tue, 10 Jun 2008, 23:41:21 EST