Numerical investigation of subsonic flow over a typical missile forebody


Tuncer İ. H. , Marvin R., Platzer M. F.

34th Aerospace Sciences Meeting and Exhibit, 1996, Nevada, United States Of America, 15 - 18 January 1996 identifier

  • Publication Type: Conference Paper / Full Text
  • Volume:
  • Doi Number: 10.2514/6.1996-189
  • City: Nevada
  • Country: United States Of America
  • Middle East Technical University Affiliated: Yes

Abstract

© 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.