| Popis: |
An improved Euler solver is presented for computing steady three-dimensional transonic flows around practical aircraft forebodies. The method is pseudo time-dependent, split and uses a finite-volume formulation. Shock waves are captured crisply, with minimal added smoothing, by means of an operator-switching facility which more accurately reflects the direction of propagation of signals. The method is robust, versatile, and holds promise for treating complex three-dimensional geometries economically. |
