Aerodynamic Analysis of Stingray UAV with Flap Deflection

This experiment explored the aerodynamic effects of flaps on a blended wing-body Stingray UAV using wind tunnel testing and flow visualization at Rensselaer Polytechnic Institute. Key Achievements: • Conducted force balance testing to compute lift, drag, and pitching moment coefficients for baseline and flapped wing configurations • Demonstrated extremely low drag coefficients and no stall behavior across both configurations, validating the aerodynamic efficiency of the Stingray UAV's blended wing-body design Skills: MATLAB, Force Balance Testing