'American Institute of Aeronautics and Astronautics (AIAA)'
Doi
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
