Aerodynamic shape optimization of the front part of an anti-tank missile based on wind tunnel testing and CFD simulation

Abstract

Wind tunnel test results of an Anti-Tank Missile model with five different warheads are presented in this paper at 0.35 Mach number and in the ±10°angle of attack range. The main goal of these experiments was to determine the final geometry among five warheads, which differs in wings geometry and wings location. Based on required aerodynamic coefficients for the existing Anti-Tank Missile, the preliminary aerodynamic configurations of the front parts (warheads) of the missile were designed based on theoretical and CFD simulation. For fine tuning and definition of the final geometry of warheads all aerodynamic configurations were tested in the T-35 subsonic wind tunnel in the Military Technical Institute. Threedimensional 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 an ATM model are also given, and agreed well with.