Analysis of Winglets for Low Reynolds UAV Flight Regimes Aaron C. Pigott Embry-Riddle Aeronautical University.

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Presentation transcript:

Analysis of Winglets for Low Reynolds UAV Flight Regimes Aaron C. Pigott Embry-Riddle Aeronautical University

Introduction and Overview Introduction Goal: Optimization of winglet sweep using STAR-CCM+ Overview Boeing AerosPACE UAV Design Why Winglets? Winglet Design The Mesh The Physics Results Conclusion

Boeing AerosPACE Collaborative senior design project with Boeing, Brigham Young University, Embry-Riddle Aeronautical University, Georgia Institute of Technology, Purdue University, and Tuskegee University Objective: Successfully collaborate and design a hand-launchable Search and Rescue UAV Winglet Analysis performed on Boeing AerosPACE UAV

UAV Design Length: 58.5 in. Span: 92.8 in. AR: 9 Main Wing Chord: 11.4 in

Why Winglets? Wingtip vortices cause induced drag Induced drag reduces aircraft range and endurance Winglets minimize wingtip vortices

Winglet Design P. Panagiotou, P. Kaparos, and K. Yakinthos found that a winglet with 50° cant angle is optimum at Re 1.2 million This study uses 50° cant angle and varies sweep of winglet

Winglet Design Baseline: Schumann Tips Case 1: No Winglet Case 2: 30° Sweep Case 3: 45° Sweep Case 4: 60° Sweep Case 2, 3, and 4: 50 degree cant angle 11.4 inches tall (equal to wing chord) 0 toe and 0 twist angle

Mesh Independence Study Incrementally changed base size to ensure solution was mesh-independent 7 million cell mesh selected based on results

Meshing Models Mesh Base Size:.009m Mesh Size: 7 million cells Prism Layer Mesher Prism Layer Thickness:.007m Prism Layer Stretching: 1.2 Surface Remesher Trimmer

Physics Models Steady Constant Density Segregated Flow K-Omega Turbulence Air conditions in Prescott, AZ to compare to wind tunnel data

Wind Tunnel A wind tunnel model was used to verify C L and C D data for the baseline model Wind Tunnel vs. CFD Data Here

Results

Conclusion Schumann tips reduced induced drag cause by wingtip vortices. C L /C D increased at each AOA Variable wingtip conclusion here

Acknowledgements Dr. Shigeo Hayashibara, ERAU Joe Becar, Brigham Young University Boeing AerosPACE Program