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Boško P. RAŠUO Goran J. OCOKOLJIĆ Aleksandar BENGIN


This paper presents modification of the existing guided missile which was done by replacing the existing front part with the new five, while the rear part of the missile with rocket motor and missile thrust vector control system remains the same. The shape of all improved front parts is completely different from the original one. Modification was performed based on required aerodynamic coefficients for the existing guided missile. The preliminary aerodynamic configurations of the improved missile front parts were designed based on theoretical and Computational Fluid Dynamics simulations. All aerodynamic configurations were tested in the T-35 wind tunnel at the Military Technical Institute (VTI) in order to determine the final geometry of the new front parts. Three-dimensional Reynolds Averaged Navier–Stokes numerical simulations were carried out to predict the aerodynamic loads of the missile based on the finite volume method. Experimental results of the axial force, normal force and pitching moment coefficients are presented. The computational results of the aerodynamic loads of a guided missile model are also given, and agreed well with.

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RAŠUO, Boško P.; OCOKOLJIĆ, Goran J.; BENGIN, Aleksandar. AERODYNAMIC SHAPE OPTIMIZATION OF GUIDED MISSILE BASED ON WIND TUNNEL TESTING AND CFD SIMULATION. Thermal Science, [S.l.], mar. 2017. ISSN 2334-7163. Available at: <>. Date accessed: 26 june 2017. doi:
Received 2017-03-02
Accepted 2017-03-13
Published 2017-03-13


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