Experiment and computation of subsonic and supersonic flow around missile calibration model

Abstract

Missile calibration model was experimentally tested and results were compared to computations including different RANS turbulence models. Computed aerodynamic characteristics were compared to the results obtained in T-38 trisonic blowdown wind tunnel of the Military Technical Institute of Serbia. The results for the range of angles-of-attack between 0º and 16º are presented. The computations were done for Mach 0.6 and 2. In the wind tunnel test section model was supported by a tail sting mounted on a pitch-and-roll mechanism by which desired aerodynamic angles can be achieved. Pressure-measurement installation, consisting of 40 ports, was built into the model. Pressure distributions were measured using an electromechanical scanning device with a solenoid-driven valve installed in the model support, behind the tail sting. A satisfactory correlation between the two sets of data was achieved leading to the conclusion that the obtained results can be useful for further numerical and experimental investigations.