Mohsin Jabur, W., Y. M, H., I. AL-Doulaimi, K. (2006). Prediction of Aerodynamic Coefficients of Missile using Panel Method. , 12(2), 389-404.
Wisam Mohsin Jabur; Hussain Y. M; Kamil I. AL-Doulaimi. "Prediction of Aerodynamic Coefficients of Missile using Panel Method". , 12, 2, 2006, 389-404.
Mohsin Jabur, W., Y. M, H., I. AL-Doulaimi, K. (2006). 'Prediction of Aerodynamic Coefficients of Missile using Panel Method', , 12(2), pp. 389-404.
Mohsin Jabur, W., Y. M, H., I. AL-Doulaimi, K. Prediction of Aerodynamic Coefficients of Missile using Panel Method. , 2006; 12(2): 389-404.

Prediction of Aerodynamic Coefficients of Missile using Panel Method

Journal of Engineering
Article 1, Volume 12, Issue 2, 2006, Pages 389-404
Authors
Wisam Mohsin Jabur; Hussain Y. M; Kamil I. AL-Doulaimi
Abstract
The low order panel method with Neumann boundary condition have been used to predict the normal force curve slope, the pitching moment curve slope, the center of pressure location and the aerodynamic load distribution for missile in compressible, steady flow. The wing-body-canard interference problem have been solved using two schemes (iterative method and internal singularity method) both are based on the panel method. The normal force curve slope, the pitching moment curve slope and the center of pressure location for a given missile has been predicted using the present numerical method and the DATCOM technique.
Keywords
Missile aerodynamic; panel method; Wing; body aerodynamic; prediction of aerodynamic coefficients; potential flow simulation
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