Aerodynamic configuration optimization design of hypersonic missile based on discrete adjoint method

This paper studied the aerodynamic configuration optimization design of hypersonic missile. The NURBS parameterization method was constructed, and an efficient and simple moving grid method was completed. Discrete adjoint method based on Euler equations was built. All these methods along with optimization method were integrated into an aerodynamic optimization system that can process complex hypersonic configuration. The forebody of a missile was optimized, and the lift to drag ratio is increased by 11.2 percent. The shape of the optimized forebody is very close to that of double cone, and this shows that a double cone forebody helps to reduce the drag. Experiment shows that discrete adjoint method has very promising prospects in optimization design of hypersonic configuration.