Numerical investigation of subsonic flow over a typical missile forebody

© 1996, American Institute of Aeronautics and Astronautics, Inc. All Rights Reserved.The NASA-Ames developed Navier-Stokes solver OVERFLOW and the panel code PMARC are applied to the computation of the flow over a typical missile forebody. The flowfields at low angles of attack from 0° to 14° are investigated. The surface pressures along the missile forebody predicted by OVERFLOW and PMARC agree well up to 10°. This favorable agreement suggests that the panel codes may be a computationally efficient tool for aerodynamic missile design purposes at low angles of attack