Comparison of Static Aerodynamic Data Obtained in Dynamic Wind Tunnel Tests and Numerical Simulation Research

The aerodynamic data obtained in the static and dynamic wind tunnel tests are presented in this paper. The tests are performed in the T-38 wind tunnel facility of the Military Technical Institute in Belgrade. Normal force and pitching moment in static and dynamic tests are measured using semiconductor five-component strain gauge balance. This specific five-component balance is dynamic derivative balance. Forced oscillation technique is used for the dynamic measurements applied in the T-38 wind tunnel. The wind tunnel data are compared with aerodynamic data determined using flow simulations with RANS (CFD) code and applied models of turbulence. The aerodynamic data calculated using semi-empirical prediction were the initial values for the numerical research. The experimental and numerical data are presented for the one standard missile model (Modified Basic Finner Model) for three flow regime Mach numbers