Abstract: By finite volume method for spatial discretization and three-stage explicit time-stepping scheme, a numerical solution of three-dimensional Euler equations is presented in this paper. The technique of local time stepping, residual averaging, enthalpy correcting, etc. is used for accelerating convergence. The analysis of von Neumann stability of one-dimensional wave equation indicates that the maximum Courant Number of the above-mentioned three-stage scheme is 2. The calculation of flows around delta wings at high angles of attack shows that the three-stage scheme and enthalpy correction method presented in this paper are better than usually used four or five-stage scheme and enthalpy damping technique. The calculated results show that the numerical method used in this paper can give a good simulation of transonic vortex flow at high angles of attack.

Key words: transonic flow, high angles of attack aerodynamics, Euler equations