Numerical simulation of aerodynamic characteristics of lateral jet at the nose section of spinning body flight vehicle

Abstract The hypersonic aircraft can achieve the effect of reducing drag by adopting a forebody ring-shaped lateral jet flow method, which. However, due to the jet interference effect, it will change the flow field structure and load distribution of the entire aircraft. Using a three-dimensional numerical simulation method based on the Navier-Stokes (NS) equations, a study on the jet interference effect from low to high jet stations and angles of attack (from 0° to 10°) was conducted for the cone-cylindrical skirt shape. The returns indicate that the higher the jet pressure ratio, the better the drag reduction effect, which is mainly concentrated in the conical and skirt sections of the aircraft; merely increasing the spike will lead to a decrease in the aircraft’s moment coefficient. As jet pressure increases, the downward force moment coefficient of the aircraft increases gradually.