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The document summarizes the calculation of zero-lift drag coefficient (Cd,0) for an unmanned aerial vehicle (UAV) design. It describes how the skin friction drag was calculated for the wings, tail, and fuselage by modeling them as flat plates and accounting for laminar and turbulent boundary layers. The total skin friction drag coefficient was found to be 0.0064. Considering additional sources of drag and lack of wind tunnel data, a conservative value of Cd,0 = 0.02 was used. MATLAB simulations agreed with

Author

Danny Jierian

Language

EN