Aerodynamic Analysis of Hypersonic Gliding Vehicles with Wide-Speed Range Based on the Cuspidal Waverider

Abstract

In order to study the variation in the lift performance as a function of the angle of attack of a hypersonic gliding vehicle under supersonic (hypersonic) conditions, the cuspidal waverider was taken as the object of this study, and the variation in the lift performance depending on the angle of attack was simulated for its design condition (M = 3.86 and H = 25 km) and hypersonic incoming flow condition (M = 8 and H = 25 km). It was also compared with the delta-wing Model 1 with the same leading-edge swept angle and Model 2 with the same spread length, respectively. The obtained results show that the zero-lift angle of attack and the critical angle of attack of the cuspidal waverider are both greater than those of the Model 1 and Model 2. The critical angle of attack increases with the free-stream Mach number for all three models. The maximum lift coefficient angle of attack on the upper surface of the cuspidal waverider decreases with increase in the Mach number, contrary to Models 1 and 2, and this relates to the degree of expansion of the free-stream flow conditions, the model layout, and the vortex structure formed on the leeward side.