Computational Techniques for Calculation of Missile Aerodynamic Coefficients
F., M., K, M., M, A. (2010). Computational Techniques for Calculation of Missile Aerodynamic Coefficients. EKB Journal Management System, 7(7th International Conference on Electrical Engineering ICEENG 2010), 1-21. doi: 10.21608/iceeng.2010.33250
Mandour, M. F.; Mahmoud, O. K; Abdalla, H. M. "Computational Techniques for Calculation of Missile Aerodynamic Coefficients". EKB Journal Management System, 7, 7th International Conference on Electrical Engineering ICEENG 2010, 2010, 1-21. doi: 10.21608/iceeng.2010.33250
F., M., K, M., M, A. (2010). 'Computational Techniques for Calculation of Missile Aerodynamic Coefficients', EKB Journal Management System, 7(7th International Conference on Electrical Engineering ICEENG 2010), pp. 1-21. doi: 10.21608/iceeng.2010.33250
F., M., K, M., M, A. Computational Techniques for Calculation of Missile Aerodynamic Coefficients. EKB Journal Management System, 2010; 7(7th International Conference on Electrical Engineering ICEENG 2010): 1-21. doi: 10.21608/iceeng.2010.33250

Computational Techniques for Calculation of Missile Aerodynamic Coefficients

The International Conference on Electrical Engineering
Article 83, Volume 7, 7th International Conference on Electrical Engineering ICEENG 2010, May 2010, Page 1-21  XML PDF (926.83 K)
Document Type: Original Article
DOI: 10.21608/iceeng.2010.33250
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Authors
Mandour, M. F.1; Mahmoud, O. K1; Abdalla, H. M2
1Egyptian Armed Forces.
2Military Technical Collage.
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 prepublished
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.
Keywords
CFD; Aerodynamic; Magnus effect
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