0601 Study on Supersonic Flow Phenomena with Corner Flow Separation in a Rectangular Ducts

Abstract

This report describes experimental results on the supersonic flow phenomena in rectangular ducts which are the models of isolators of cramjet engine, using the pressure-vacuum type Mach 4 supersonic wind tunnel. This investigation shows the effects of duct cross-section aspect ratio and length on the supersonic flow structure in the rectangular ducts by schlieren photographs, duct wall pressure fluctuation measurements and detailed total pressure distribution measurements.