Investigation of Scramjet Injection Strategies for High Mach Number Flows

Author

David W. Riggins, Missouri University of Science and TechnologyFollow
C. R. McClinton
R. C. Rogers
R. D. Bittner

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