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, 14(14th International Conference on Applied Mechanics and Mechanical Engineering.), 1-19. doi: 10.21608/amme.2010.38119
Mandour, M. F.; Mahmoud, O. K; Abdalla, H. M. "Computational Techniques for Calculation of Missile Aerodynamic Coefficients". EKB Journal Management System, 14, 14th International Conference on Applied Mechanics and Mechanical Engineering., 2010, 1-19. doi: 10.21608/amme.2010.38119
F., M., K, M., M, A. (2010). 'Computational Techniques for Calculation of Missile Aerodynamic Coefficients', EKB Journal Management System, 14(14th International Conference on Applied Mechanics and Mechanical Engineering.), pp. 1-19. doi: 10.21608/amme.2010.38119
F., M., K, M., M, A. Computational Techniques for Calculation of Missile Aerodynamic Coefficients. EKB Journal Management System, 2010; 14(14th International Conference on Applied Mechanics and Mechanical Engineering.): 1-19. doi: 10.21608/amme.2010.38119

Computational Techniques for Calculation of Missile Aerodynamic Coefficients

The International Conference on Applied Mechanics and Mechanical Engineering
Article 72, Volume 14, 14th International Conference on Applied Mechanics and Mechanical Engineering., May 2010, Page 1-19  XML PDF (846.79 K)
Document Type: Original Article
DOI: 10.21608/amme.2010.38119
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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 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.
Keywords
CFD; Aerodynamic; Magnus effect
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