Published October 1983
| Published
Journal Article
Open
The Response of Normal Shocks in Diffusers
- Creators
- Culick, F. E. C.
- Rogers, T.
Abstract
The frequency response of a normal shock in a diverging channel is calculated for application to problems of pressure oscillations in ramjet engines. Two limits of a linearized analysis arc discussed: one represents isentropic flow on both sides of a shock wave; the other may be a crude appr'l'I;imation to the influence of flow separation induced hy the wave. Numerical results arc given, and the influences of the shock wave on oscillations in the engine are discus,ed.
Additional Information
© American Institute of Aeronautics and Astronautics, Inc., 1983, submitted May 6, 1982; revision received Jan. 26, 1983. Presented as Paper 81-1431 at the AIAA/SAE/ASME 17th Joint Propulsion Conference, Colorado Springs, Colo., July 27-29, 1981. I am indebted to Dr. M. Sajben for several useful discussions, particularly concerning the approximation of quasisteady behavior, and to V. Yang for his help in completing some of the calculations. This work was supported partly by the Navy Liquid Fuel Ramjet Component Technology Program (N00123-77-C-0541) and partly by the Air Force Office of Scientific Research, Grant AFOSR-80- 0265.Attached Files
Published - 265_Culick_FEC_1981.pdf
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265_Culick_FEC_1981.pdf
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Additional details
- Eprint ID
- 21242
- Resolver ID
- CaltechAUTHORS:20101208-111845159
- Navy Liquid Fuel Ramjet Component Technology Program
- N00123-77-C0541
- Air Force Office of Scientific Research (AFOSR)
- AFOSR-80-0265
- Created
-
2010-12-10Created from EPrint's datestamp field
- Updated
-
2021-11-09Created from EPrint's last_modified field
- Caltech groups
- Guggenheim Jet Propulsion Center, GALCIT
- Other Numbering System Name
- Guggenheim Jet Propulsion Center