Inlet/Engine Interactions in an Axisymmetric Pulse Detonation Engine System

The effects of oscillatory backpressure on the air induction system for pulse detonation engines were examined for an axisymmetric, external compression cone guration at a freestream Mach number of 2.1. The pressure perturbations at the diffuser exit were produced by a rotating mechanism simulating a valve, which periodically opened and closed the detonation tubes. Theoscillation frequency wasvaried from 30 to 100 Hzfor each individual tube. Through varying the downstream blockage, the spillage was altered, and different mass e ows wereobtained. In all casestheresults indicated that e uctuations in thestatic and stagnation pressures in the inletwere within 3%, without e ow instability noted near the inlet capture.