Wind Tunnel Testing of an Aerial Platform at Wide Range of Angles of Attack and Angles of Sideslip

Wind Tunnel Testing (WTT) is an experimental way to find the aerodynamic forces and moments produced about the Centre of Gravity (CG) at wide ranges of Reynolds Number (Re). In this research, a scaled-down model of an aerial platform is tested in a CAE closed-circuit subsonic wind tunnel, emphasizing measuring aerodynamic forces and moments under different flight conditions. With a focus on wind tunnel sting balance calibration and wind tunnel corrections using a calibration matrix and corrective factors, the testing was carried out to examine the aircraft data and behavior at a range of free stream velocities and aerodynamic angles. Angle of attack varied from −13 to +18 degrees while angle of sideslip varied from −13 to +18 degree. For sideslip testing, the model was mounted on a sting balance with 90 degrees rotation and tested for angle of attack. The goal of the research is to shed light on the platform’s aerodynamic properties as a function of various configurations which are planned by varying different payload combinations. Reynolds number and velocity matching were used in the study to guarantee dynamic similarity between the scaled model and the actual platform, enabling a precise depiction of full-scale aerodynamic behavior. The results contribute to the understanding of aerodynamic forces such as lift, drag, side force and aerodynamic moments produced by these forces which are pitching, rolling, and yawing. Their dependencies upon flight conditions and aerodynamic angles are also investigated and commented upon. The results obtained are consistent with the aerodynamic principles and trends of such platform once matched with the data available in open literature. The methodology used in this work will serve as a foundation for further aerodynamic testing on configurations with payload combinations. The only deviation from conventional results is observed in the drag channel where the coefficient of drag was observed as zero at all negative angles of attack, depicting the non-functional state of the strain gauge associated with the drag channel of the sting balance. Results of other coefficients follow conventional trend.