Scramjet measurements in a shock tunnel
Author:
Affiliation:
1. Queensland, Univ., Brisbane, Australia
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1999-2450
Reference32 articles.
1. Osgerby,I.T., Smithson,H.K. andWagner,D.A. 1970Supersoniccombustiontestwith a doubleoblique-shockscramjetin a shocktunnel,AIAA Jv8no.9pp1703-1705.
2. SkinnerK.A., andStalkerR.J.(1994)A time of flight massspectrometerfor impulsefacilities. AIAA J,V32,No.11,pp.2325-2328
3. Paull,A. 1996A SimpleShockTunnelDriver Gas DetectorShockWavesv6no.5~~309-312.
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1. Extrapolation of a generic scramjet model to flight scale by experiments, flight data and CFD;Shock Waves;2009
2. Investigation of Scramjet Flow Path Stability in a Shock Tunnel;36th AIAA Fluid Dynamics Conference and Exhibit;2006-06-05
3. Numerical Simulation of Transient Scramjet Combustion in a Shock Tunnel;43rd AIAA Aerospace Sciences Meeting and Exhibit;2005-01-10
4. Development of Direct-Measuring Skin-Friction Gauges for Hypersonic Flight Tests;AIAA Journal;2003-08
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