REPUBLIC OF SERBIA

MINISTRY OF DEFENCE

www.mod.gov.rs

MINISTRY OF DEFENCE

Material Resources Sector

Defensive Technologies Department

Military Technical Institute

www.vti.mod.gov.rs

AERODYNAMIC CHARACTERISTICS OF THE MISSILES MOVABLE WING IN THE PRESENCE OF THE FIXED WING

ALİ AKGÜL

ROKETSAN Missile Industries Inc., Ankara-Türkiye, aakgul@ roketsan.com.tr

emrah gülay

ROKETSAN Missile Industries Inc., Ankara-Türkiye, egulay@ roketsan.com.tr

JOVAN ISAKOVIĆ

Military Technical Institute, Belgrade-Serbia, vti@vti.vs.rs

SLOBODAN MANDIĆ

Military Technical Institute, Belgrade, Serbia, msmanda@open.telekom.rs

Abstract: In order to investigate the effect of canards on the wing aerodynamic performance, Computational Fluid Dynamics (CFD) simulations and wind tunnel experiments were performed at Mach number 0.6 and 1.9. Cylindrical body with ogival nose, wing section and canard geometry is used in this study. By changing span dimension and the location of the canard on the body, 5 different body-wing-canard and 1 body-wing configuration are obtained. Wind tunnel measurements and computations of normal force, hinge and bending moment coefficients are done for those configurations. The CFD calculations are performed by the FLUENT software package. Comparing the results from analysis and the experiment, it shows that predictions are in good agreement.

Key words: Missile wing aerodynamics, CFD calculation, Wind Tunnel Experiments, FLUENT.