Navier-Stokes and Euler Computations of the Flow Field Around a Complete Aircraft

The flow field around a complete supersonic V/STOL configuration was computed by solving the Euler and thin-layer Navier-Stokes equations with a multizone, finite-volume, explicit Runge-Kutta time-stepping method. The Navier-Stokes equations were solved in specified zones and the Euler equations were solved in the remaining zones. The Baldwin-Lomax turbulence model was applied for the Navier-Stokes computations. A global grid for the complete aircraft configuration was generated with an optimization method and divided into a multizone grid. The computed lift coefficients and pressure on the wing surface were compared with experimental data.