Performance of three-dimensional compressible Navier-Stokes codes at low Mach numbers

Two three-dimensional compressible Navier-Stokes solvers accurately predict the low mach-number performance of an untwisted rectangular wing and a subsonic transport wing-fuselage configuration. The computed pressure distributions are almost identical and agree well with the experimental data. The predicted pressure distributions are also extremely close to those predicted by an incompressible Navier-Stokes solver. The three flow solvers predict almost similar boundary profiles and the computational time is case dependent. The compressible solvers employ a finite volume formulation.