Application of CFD to High Angle of Attack Missile Flow Fields

Report No. ARL-RP-3
Authors: Sahu, Jubaraj; Heavey, Karen; Dinavahi, Surya
Date/Pages: September 2000; 22 pages
Note: Reprint from the American Institute of Aeronautics and Astronautics Atmospheric Flight Mechanics Conference, no. AIAA 2000-4210, Denver, CO, August 2000.
Abstract: Computational fluid dynamics (CFD) calculations have been performed for a missile body with and without fins. Numerical flow field computations have been made for various Mach numbers and roll angles using an unsteady zonal Navier-Stokes code (ZNSFLOW) and the chimera composite grid discretization technique at supersonic velocity and high angle of attack. Steady-state numerical results have been obtained and compared for cases modeling an ogive- cylinder missile with and without fins. Computed results show the details of the expected flow field features to include vortical crossflow separation. Computed results are compared with experimental data obtained for the same configurations and conditions and are generally found to be in good agreement with the data. The results help to show the predictive capabilities of CFD techniques for supersonic projectiles at incidence.
Distribution: Approved for public release
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Last Update / Reviewed: September 1, 2000