Numerical investigation of subsonic flow over a typical missile forebody

Date

1996-01-01

Author

Tuncer, İsmail Hakkı
Platzer, Max F.

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© 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.

URI

https://hdl.handle.net/11511/57578

DOI

https://doi.org/10.2514/6.1996-189

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Department of Aerospace Engineering, Conference / Seminar

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Citation Formats

İ. H. Tuncer and M. F. Platzer, “Numerical investigation of subsonic flow over a typical missile forebody,” 1996, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/57578.