Investigation of Scramjet Injection Strategies for High Mach Number Flows
Abstract
A method for estimating the axial distribution of thrust performance potential in a supersonic combustor is described. A complementary technique for illustrating the spatial evolution and distribution of thrust potential and loss mechanisms in reacting flows is developed. A wall jet case and swept ramp injector case for Mach 17 and Mach 13.5 flight enthalpy inflow conditions, respectively, are numerically modeled and analyzed using these techniques. © 1995 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.
Recommended Citation
D. W. Riggins et al., "Investigation of Scramjet Injection Strategies for High Mach Number Flows," Journal of Propulsion and Power, vol. 11, no. 3, pp. 409 - 418, American Institute of Aeronautics and Astronautics, Jan 1995.
The definitive version is available at https://doi.org/10.2514/3.23859
Department(s)
Mechanical and Aerospace Engineering
International Standard Serial Number (ISSN)
0748-4658
Document Type
Article - Journal
Document Version
Citation
File Type
text
Language(s)
English
Rights
© 2024 American Institute of Aeronautics and Astronautics, All rights reserved.
Publication Date
01 Jan 1995
