摘要: Wind tunnel tests with scaled models of ISRO's scramjet based air breathing vehicle indicated the intake to be unstarting in the envisaged operational AoA range. Based on the pressure distribution and flow field data available, re... 展开 Wind tunnel tests with scaled models of ISRO's scramjet based air breathing vehicle indicated the intake to be unstarting in the envisaged operational AoA range. Based on the pressure distribution and flow field data available, reasons for intake unstarting were identified and plausible modifications to the intake geometry were suggested. These modifications were implemented sequentially through a parametric study to assess the effect of each modification on the intake performance and a robust optimal configuration meeting the operational requirements with respect to AoA range and combustor flow entry conditions (Mach number & pressure) is evolved. 收起