THERMAL SCIENCE

International Scientific Journal

Goran J. Ocokoljić

,

Boško P. Rašuo

,

Aleksandar Č Bengin

AERODYNAMIC SHAPE OPTIMIZATION OF GUIDED MISSILE BASED ON WIND TUNNEL TESTING AND COMPUTATIONAL FLUID DYNAMICS SIMULATION

ABSTRACT
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 in order to determine the final geometry of the new front parts. The 3-D 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.
KEYWORDS
experimental aerodynamics, wind tunnel testing, CFD, aerodynamic coefficients, missile model
PAPER SUBMITTED: 2015-05-15
PAPER REVISED: 2015-11-22
PAPER ACCEPTED: 2015-11-22
PUBLISHED ONLINE: 2015-12-13
DOI REFERENCE: https://doi.org/10.2298/TSCI150515184O
CITATION EXPORT: view in browser or download as text file
THERMAL SCIENCE YEAR 2017, VOLUME 21, ISSUE Issue 3, PAGES [1543 - 1554]
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Aerodynamic shape optimization of guided missile based on wind tunnel testing and computational fluid dynamics simulation

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