![]() ![]() ![]() Five Angle of Attacks were considered for both the cases. Also, a detailed analysis of vortex formation across the wingtip for both the scenarios was performed. Both the models were compared to see the effect of winglets in drag reduction which ultimately agreed to increase the lift and endurance efficiency of the flying wing body with the application of winglet. Both the flying wing geometries i.e., with and without winglets were modeled and solved in CFD code. The parameters for winglets were calculated using the standard values from the previous research. Therefore, we have taken up this as the main subject for our paper. Previously, not much work has been done on winglet design of Hand-Launched UAVs and the vorticity analysis. Our study made us realize that winglet configuration can play a major role in reducing the drag of the body and, finally increasing the overall mission time of the UAV. During the design phase, it was understood that a UAV with increased endurance will be more helpful in practical use. After defining design requirements, these values are used t o stipulate parameters in designing equations of UAV sizing and airfoil selection. A Design space was mathematically plotted by defining parameters: cruising speed, stall speed, GTOW, aspect ratio etc. The UAV is highly portable and can be launched for a mission from almost anywhere. In the present work, a Flying wing body was designed that can be used for surveillance and reconnaissance. ![]()
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