Computational Techniques for Calculation of Missile Aerodynamic Coefficients

F., Mandour, M.; K, Mahmoud, O.; M, Abdalla, H.

doi:10.21608/amme.2010.38119

Computational Techniques for Calculation of Missile Aerodynamic Coefficients

Document Type : Original Article

Authors

¹ Egyptian Armed Forces.

² Military Technical Collage.

10.21608/amme.2010.38119

Abstract

Abstract:
Studying the flow over bodies of revolution is crucial to the design of missiles and obtaining the correct shape which has a large impact on the performance of the missile. Three-dimensional flow simulation over a body of revolution were carried out in order to obtain flow field parameters for different angles of attack namely -4.09, -2.04, 2.06, 4.11, 6.17 and 12.41˚ at Mach number of 0.5 (subsonic) and of -4.34, -2.15, 2.17, 4.37, 8.87, and 13.6˚ at Mach number of 1.2 ( transonic flow conditions). The software FLUENT with its prepressor GAMBIT were used to model a missile of known geometry. The Computational Fluid dynamics results were validated with a pre-published experimental data measured by a wind tunnel [1] The validated model was used to examine Magnus effect on the spinning missile which improves the effect of the high spinning rate on the side force affecting the missile body.

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