Drag force on quasi-axisymmetric scramjets at various flight Mach numbers: Theory and experiment

Tanimizu, K, Mee, DJ, Stalker, RJ and Jacobs, PA (2009) Drag force on quasi-axisymmetric scramjets at various flight Mach numbers: Theory and experiment. SHOCK WAVES, 19 2: 83-93. doi:10.1007/s00193-009-0194-x


Author Tanimizu, K
Mee, DJ
Stalker, RJ
Jacobs, PA
Title Drag force on quasi-axisymmetric scramjets at various flight Mach numbers: Theory and experiment
Journal name SHOCK WAVES   Check publisher's open access policy
ISSN 0938-1287
Publication date 2009-06-01
Year available 2009
Sub-type Article (original research)
DOI 10.1007/s00193-009-0194-x
Open Access Status DOI
Volume 19
Issue 2
Start page 83
End page 93
Total pages 11
Editor K. Takayama
Evgeniy Timofeev
Place of publication Germany
Publisher Springer
Language eng
Subject C1
290200 Aerospace Engineering
090107 Hypersonic Propulsion and Hypersonic Aerodynamics
880399 Aerospace Transport not elsewhere classified
Abstract The net axial force on a non-fuelled quasi-axisymmetric scramjet model designed for operation at Mach 6 was measured in the T4 Stalker tube at The University of Queensland using a single-component stress wave force balance. The design used was a variant of a model that was tested previously at Mach 6. The new model was equipped with a modified thrust nozzle that was designed to improve the performance of the nozzle. Tests were performed to measure the drag force on the model for Mach 6, Mach 8 and Mach 10 shock tunnel nozzles for a range of flow conditions. The nozzle-supply enthalpy was varied from 3 to 10 MJ/kg and the nozzle-supply pressure from 35 to 45 MPa. For the test model, the drag coefficient increased with increasing nozzle-supply enthalpy. The test results are compared with a force prediction method based on simple hypersonic theories and three-dimensional CFD. The test results are in good agreement with the predictions over the wide range of conditions tested. The re-designed model has a more efficient nozzle but this comes at the expense of increased drag associated with the modifications required for the cowl. The results indicate that this type of vehicle design is not likely to be suitable for flight above Mach 8.
Keyword Scramjet
TURBULENT-BOUNDARY-LAYER
Force measurement;
Flow visualization
Q-Index Code C1
Q-Index Status Confirmed Code
Grant ID DP0452374
Institutional Status UQ

Document type: Journal Article
Sub-type: Article (original research)
Collections: 2010 Higher Education Research Data Collection
School of Mechanical & Mining Engineering Publications
 
Versions
Version Filter Type
Citation counts: TR Web of Science Citation Count  Cited 8 times in Thomson Reuters Web of Science Article | Citations
Scopus Citation Count Cited 11 times in Scopus Article | Citations
Google Scholar Search Google Scholar
Created: Thu, 03 Sep 2009, 18:03:54 EST by Mr Andrew Martlew on behalf of School of Mechanical and Mining Engineering