MULTIBLOCK EULER COMPUTATION OF TRANSONIC FLOW ABOUT A GENERIC AIRCRAFT CONFIGURATION

SUMMARY

An implicit, upwind numerical scheme is presented for computing the unsteady transonic flowfield around complex aircraft configurations. This scheme solves the time-dependent Euler equations with a finite volume method that incorporates a high resolution Riemann solver to define the interface fluxes. A multiblock domain decomposition appproach is used to partition the computational domain into a completely arbitrary arrangement of blocks. However, this work is restricted to C¹-continuous grid lines across block boundaries. Consequently, block-block interfaces are treated such as to mimic interior block communication, thus introducing no additional spatial differencing error. Computational results have been obtained for a complete wing-pylon-store configuration with the store in the captive and vertical launch positions. The numerical results for both stationary and dynamic grids have shown favorable agreement with experimental data.