Navier-stokes calculations of transonic viscous flow about wing/body configurations

A three-dimensional Navier-Stokes solver has been developed for viscous transonic flow about transport and fighter wing/body configurations. The thin- and slender-layer approximations to the unsteady compressible Reynolds-averaged Navier-Stokes equations are solved by an explicit multistage Runge-Kutta method using a finite-volume formulation on body-conforming curvilinear grids. Efficiency is enhanced by employing local time stepping and vectorization. Microtasking enables the code to make optimal use of multiple processors. Comparisons of computed surf ace pressure distributions with experimental data for typical transport and fighter configurations show that the Navier-Stokes solutions improve prediction of shock strength and location over simpler Euler equation models.