Comparison of drag measurements of two axisymmetric scramjet models at Mach 6

Tanimizu, K., Mee, D. J. and Stalker, R. J. (2007). Comparison of drag measurements of two axisymmetric scramjet models at Mach 6. In: Peter Jacobs, Tim McIntyre, Matthew Cleary, David Buttsworth, David Mee, Rose Clements, Richard Morgan and Charles Lemckert, 16th Australasian Fluid Mechanics Conference (AFMC). 16th Australasian Fluid Mechanics Conference (AFMC), Gold Coast, Queensland, Australia, (1299-1303). 3-7 December, 2007.

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Author Tanimizu, K.
Mee, D. J.
Stalker, R. J.
Title of paper Comparison of drag measurements of two axisymmetric scramjet models at Mach 6
Conference name 16th Australasian Fluid Mechanics Conference (AFMC)
Conference location Gold Coast, Queensland, Australia
Conference dates 3-7 December, 2007
Convener School of Engineering, University of Queensland
Proceedings title 16th Australasian Fluid Mechanics Conference (AFMC)
Journal name Proceedings of the 16th Australasian Fluid Mechanics Conference, 16AFMC
Place of Publication Brisbane, Australia
Publisher School of Engineering, The University of Queensland
Publication Year 2007
Year available 2007
Sub-type Fully published paper
Open Access Status File (Author Post-print)
ISBN 978-1-864998-94-8
Editor Peter Jacobs
Tim McIntyre
Matthew Cleary
David Buttsworth
David Mee
Rose Clements
Richard Morgan
Charles Lemckert
Start page 1299
End page 1303
Total pages 4
Collection year 2007
Language eng
Abstract/Summary Axial forces on quasi-axisymmetric scramjet models designed for operation at Mach 6 and Mach 8 were measured in the T4 Stalker tube at The University of Queensland using a single component stress wave force balance. A Mach 6 nozzle was used. The nozzle supply enthalpy was varied from 3 to 9 MJ/kg and the nozzle supply pressure from 35 to 45 MPa. As the conditions varied, the Mach number varied from 5.7 to 6.7. For both test models, the drag coefficients decreased with increasing Mach number. However, significant differences between the models were not observed over a range of free stream Mach numbers. A theoretical procedure to calculate the drag coefficient was found to give good agreement with experiments when appropriate account was taken of flow spillage at the intake.
Subjects 290201 Aerodynamics
290299 Aerospace Engineering not elsewhere classified
780102 Physical sciences
E1
Q-Index Code E1

 
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Created: Wed, 19 Dec 2007, 15:29:52 EST by Laura McTaggart on behalf of School of Engineering