.Drag polar (lifting coefficient C, versus drag coefficient CD) of a UAV airplane is shown in...

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.Drag polar (lifting coefficient C₁, versus drag coefficient CD) of a UAV airplane is shown in Fig. 3 and expressed as: 6.03 0.03 Ca 44 CD=CDo + CD=CDo + KC² where CD. (zero lift drag coefficient)=0.03, and induced drag coefficient factor K = 0.027. (a) Calculate the maximum L/D for this UAV airplane. (10%) (b) What is lifting coefficient (CL) and drag coefficient (CD) for the maximum L/D condition? (5%) .Drag polar (lifting coefficient C₁, versus drag coefficient CD) of a UAV airplane is shown in Fig. 3 and expressed as: 6.03 0.03 Ca 44 CD=CDo + CD=CDo + KC² where CD. (zero lift drag coefficient)=0.03, and induced drag coefficient factor K = 0.027. (a) Calculate the maximum L/D for this UAV airplane. (10%) (b) What is lifting coefficient (CL) and drag coefficient (CD) for the maximum L/D condition? (5%)

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The question is asking for the maximum lifttodrag ratio LD for a UAV airplane given the drag polar equation and certain constants The drag polar of an ... View the full answer