Aerodynamics And Aerodynamic Heating Research For The Wing Of Hypersonic Projectile

As the weapon technology improves, the launch velocity is raised greatly. Strict performance of aerodynamics and thermal protection is put forward in hypersonic situation. The wings of projectile provide the lift, control the direction and keep the stability of flying. A method of aerodynamics and aerodynamic heating simulating for wings of hypersonic projectile in denseness aerosphere is studied.An elliptical differential equation method of grid generation is applied. The three dimensional Euler equations are solved by the MacCormack scheme and variables of flow field are obtained. The coefficients of drag, lift, pitching moment, pressure center are calculated by the integral of every wing surface according to the flow field parameters. The results accord with the aerodynamic theory.Based on the parameters of the numerical calculation, using semi-empirical heating rates calculating formulas and reference enthalpy method , the heating rates and temperature distributions are obtained. The analyses indicate that Mach number and leading edge sweep angle are important factors for aerodynamic heating. The results are rewarding for engineer to reference.