Study of flow unsteadiness in a bifurcated Y-Shaped duct for a typical combat aircraft model

Aircraft intake which operates at supersonic speed encounters a flow instability phenomenon called “Buzz”. In this study wind tunnel tests have been carried out on a typical combat aircraft model for air intake studies. An attempt has been made towards qualitative and quantitative assessment of buzz characteristics. The present study is intended to study the qualitative and quantitative aspects of the buzz characteristics. In quantitative study unsteady pressures measured by rake, fuselage ports, duct pressures have been analyzed and Schlieren technique has been used to study the qualitative aspect of the buzz characteristics. It is observed that the pressure recovery is decreasing and pulse level is increasing during the onset of buzz at supersonic speed regime