Study of shock wave/boundary layer interactions on high-pressure capturing wings

Abstract eng:
To evaluate the heating load of high-pressure capturing wings (HCW) at various design conditions, a series of numerical cases were carried out to study the shock wave/boundary layer interactions between the inclined shock wave compressed by the airframe and the HCW. The results show that the maximal value of the heat-flux on the lower surface of the HCW decreases with the increase of the blunt radius of the HCW, the backward position of the inclined shock wave, and the decrease of the Reynolds number. While it increases with the increase of both the Mach number and the half cone angle. Besides, the maximal value of the heat-flux on the lower surface of the HCW is significantly lower than the value on the stagnation point. The present results show that the HCW configuration should have a good application prospect.

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