THE SOLUTION OF EULER EQUATIONS BY THIRD, FOURTH, AND FIFTH STAGE RUNGE-KUTTA TIME-STEPPING

The computation of inviscid transonic flow containing strong shock waves or a complex vortex structure calls for the solution of the Euler equations as a physical model. Transonic wing computations are performed in the Euler approximation. This method is based on finite volume method and Runge-Kutta time-splitting (third, fourth, and fifth stages). The calculations are performed on a 80486/DX PC and are compared with experimental data. Comparisons are also made of the stability and time-saving of each Runge-Kutta method and their combinations.