NUMERICAL SOLUTION OF THE EULER EQUATIONS FOR THE TRANSONIC FLOW ABOUT THE COMPLETE AIRCRAFT AT HIGH ANGLES OF ATTACKE

In this paper, the conformal mapping technique combined with the algebraic method is used, the unified body fitted orthonormal O H mesh is generated. The Euler equations are solved by finite volume method, the transonic flow about the fighter like aircraft and wing body configuration at high angles of attack can be simulated. The results of the computations show good agreement with experimental normal force coefficients, aerodynamic center position and surface pressure distributions.