Abstract
Oblique detonation waves are possible ignition mechanisms for scramjet engines. Results from a numerical study of the effects of changing the inflow pressure on oblique detonation wave structure for supersonic flow of a stoichiometric hydrogen-air mixture over a flat plate followed by a ramp are presented. Viscous effects and finite-rate chemistry are considered. Inflow pressure is varied from 0.1 to 1 atmosphere for Mach 4 inflow over a 30-degree ramp. Also, the effect of wall heat transfer rate is examined by comparing adiabatic wall, and constant temperature wall solutions. A separation bubble forms at the intersection of the flat plate and the ramp. The bubble size is a maximum for an inflow pressure of 0.5 atm. Increased inflow pressure strengthens and steepens the shock wave. The bubble size is smaller for the adiabatic wall case than it is for the constant wall temperature condition. Oblique detonation waves occur for the higher inflow pressure cases for both wall temperature conditions.
Recommended Citation
B. S. Green and H. F. Nelson, "Effect of Inflow Pressure and Wall Heat Transfer on Shock-Induced Combustion/detonation," 34th Aerospace Sciences Meeting and Exhibit, American Institute of Aeronautics and Astronautics, Jan 1996.
The definitive version is available at https://doi.org/10.2514/6.1996-111
Department(s)
Mechanical and Aerospace Engineering
Publication Status
Open Access
Document Type
Article - Conference proceedings
Document Version
Citation
File Type
text
Language(s)
English
Rights
© 2024 American Institute of Aeronautics and Astronautics, All rights reserved.
Publication Date
01 Jan 1996
