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AERODYNAMIC COEFFICIENTS DETERMINATION FOR ANTITANK
GORAN OCOKOLJIĆ Military Technical Institute, Belgrade, e-mail: ocokoljic.goran@gmail.com SAŠA ŽIVKOVIĆ Military Technical Institute, Belgrade, e-mail: sasavite@yahoo.com SREDOJE SUBOTIĆ Military Technical Institute, Belgrade, e-mail: sredoje.subotic@gmail.com
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Abstract: In this paper, aerodynamic test and numerical results of an antitank missile model with thrust vector control (TVC) jet simulation are presented. The test was performed in a subsonic wind tunnel, and high pressure air is used for jet simulation. The purpose of the experiment was to provide an experimental data base for estimation of the numerical results reliability. In next step, with proven numerical model, aerodynamic coefficients for missile with solid propellant rocket motor jets will be determined. Analysis was presented for Mach number 0.2, model configurations with and without jets, and three jet tabs positions: tabs out of the jets, upper or lower tabs in the jets. Results are presented by pitching moment coefficients. Comparison of the experimental and numerical results shows satisfactory agreement.
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