Aerodynamic Performance Analyses of Blunt Cone with New Cavity-channel Conception in the Hypersonic Flow

Abstract

When the hypersonic vehicle flies at high speed, there are serious problems of aerodynamic heating and drag near the nose stagnation point. Although the blunt body can reduce the heat flux near the nose, great aerodynamic drag will be produced. Similarly, the sharp edge can reduce aerodynamic drag, but the aerodynamic heating is more severe. In this paper, a new conception of cavity-channel configuration with heating and drag reduction is proposed to solve this contradiction. The aerothermal and aerodynamic performance of blunt cone applying the cavity-channel configuration is calculated and analyzed via solving N-S equation. The numerical results show that the new concept configuration can achieve the expected effect of heating and drag reduction. The higher the channel height, the better the effect of drag reduction, however, the effect of heating reduction is weakened until the heating increment appears. This paper preliminarily investigates the principle of heating and drag reduction of cavity-channel configuration and summarizes the law of applying the concept of cavity-channel to heating and drag reduction.