Euler solutions for transonic flow past a fighter wing

A procedure for the numerical solution of steady and unsteady transonic flows past a fighter wing is described. This procedure solves the three-dimensional, unsteady Euler equations in a body-fitted coordinate system. A finite-difference procedure of second-order spatial accuracy and first-order temporal accuracy is used to discretize the governing equations and a hybrid time-marching scheme is used to advance the solution from one time level to the next. In unsteady transonic flow applications involving oscillating wing surfaces, the surface motion is imposed on the solution as a transpiration boundary condition. A number of steady and unsteady calculations are presented for the F-5 fighter wing at transonic Mach numbers and detailed comparison with experiments are given.