Numerical solution for complete aircraftʹs subsonic-transonic-supersonic flow at high angles of attack Original Research Article

In this paper, the conformal mapping technique combined with the algebraic method is used to generate the unified body fitted orthonormal O-H mesh for fighter-type aircraft. The flow field and aerodynamic characteristics of complete aircraftʹs subsonic-transonic-supersonic flow at angles of attack up to 59 ° have been successfully calculated by applying finite volume method to solve the Euler equations with high efficiency. The feasibility of using solution of Euler equations to simulate separated flow at high angles of attack is further discussed. The calculation shows that the method described here can automatically capture highly swept-back wing leading edge separated flow vortices, body vortices, and their mutual interactions. The results of calculation are in good agreement with experimental wing surface pressure distributions and the normal force coefficients and aerodynamic center position.