Study on the drag and heat reduction performance of porous opposing jet in hypersonic flow

Abstract In the present study, porous jet strategy is applied to reduce the drag and aero-heating characteristics at the blunt leading edge of the hypersonic vehicle. The two-equation SST k-w turbulence model has been utilized to study the detailed information of flowfield, and the numerical method has been validated against the available experimental data in the open literature. The influence of the jet total-pressure ratio, the angle of attack, and the freestream Mach number on the characteristics of drag and heat reduction are investigated numerically by the numbers. The obtained results show that there is an obvious three-dimension transverse effect around the blunt leading edge. In addition, the performance of drag and heat reduction is better with the increase of jet total-pressure ratio. And the angle of attack would weaken the interaction of porous jets near the blunt body and results in degradation of drag and heat reduction performance that is not good for the drag and heat reduction of porous opposing jet. Under the equal dynamic pressure design condition, the drag reduction performance is better with the increase of freestream Ma, however the flowfield distributions are similar for different freestream Ma.