Wind tunnel support system effects on a fighter aircraft model at Mach numbers from 0.6 to 2.0

A wind tunnel investigation was conducted using a fighter aircraft model with various sting and blade support system arrangements to evaluate the effects of the model support system on the total body and component longitudinal force and moment data. Total aerodynamic force and moment data were determined from corrected strain gage balance measured loads. Component data (i.e. tail loads) were obtained by subtracting tail off balance, data from tail on data. Data taken at freestream Mach numbers from 0.6 to 2.0 and model angles of attack from -2 to 8 degrees were examined. The analysis indicates a significant change in total body and component force coefficients in the presence of various support system configurations. The upper blade tends to decrease drag, lift, and pitching moment coefficients, while the lower blade generally increases these coefficients. The influence of the sting on aerodynamic coefficients is a function of Mach number and angle of attack. A correction methodology using sting/blade "tares" is proposed and evaluated. The evaluation shows that total body and component force and moment coefficient data are significantly improved using sting/ blade "tares" to correct for support system effects.