Internal and External Flow Simulation Using Multizone Euler/Navier-Stokes Aerodynamic Methods

A computational method based on a cell-centered, finite-volume spatial discretization and explicit time-stepping algorithm for solving the Euler and Navier-Stokes equations is used to simulate inviscid and viscous flow about configurations including a diverging nozzle, a 74 degree delta wing, and a Mach 6 Waverider. Solutions are obtained using patched multizone grids with both matching and different grid densities across zonal interfaces and are correlated with analytical solutions and experimental data. The computational results increase the confidence in applying Euler and Navier-Stokes solvers to the more complex mixed internal/external flows associated with complete aircraft configurations.