Effect of Combustion Condition on Cf in a Hypersonic Air-Breathing Enzine

Abstract

The effect of combustion on characteristic values of supersonic flow field and their relationship with wall skin friction was examined. The measurements were performed in a hypersonic combustor with air-flow Mach number, unit Reynolds numbers, fuel equivalence ratio of 2.5, 1.6×10 7 – 3.5×10 7 m -1 ,0-0.6 respectively. The direct measurements of skin friction were conducted using a skin friction gage with accuracy which was found to be ±5%. The state of the air flow in the boundary layer and several points in the main flow was also surveyed at the local position, and the effect of combustion condition on Cf was examined.