Navier-stokes simulation of transonic vortex flow over a delta wing

An explicit multi-stage Runge-Kutta time-stepping scheme with cellcentred finite volume spatial discretisation is employed to solve three-dimensional, compressible Navier-Stokes equations. A novel variation for computation of viscous fluxes is used. Convergence to steady state is expedited through acceleration techniques. The vortex flow over a 65xB0; cropped rounded leading edge delta wing is computed, and the results are compared with experimental data and Euler solution