Numerical Simulation of Compressible Flow Field about Complete ASKA Aircraft Configuration

Numerical simulations of compressible inviscid flows are carried out for the complete configuration of experimental aircraft ‘ASKA’ which adopts the USB technology to increase the amount of lift force. Three different grid systems corresponding to different configurations are generated by a newly developed interactive grid generation method. Euler equations are solved by the second order upwind biased finite volume method. A planar Gauss-Seidel relaxation method is adopted to realize a rapid convergence to steady solutions. Computations are made to see the influences of different arrangements of engine nacelles over the interfered flow fields.