Aerodynamics Calculator

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Calculate Parasite Drag Coefficient for horizontal and vertical tail contribution

The drag polar of an airplane relates the drag coefficient (CDC_DCD​) to the lift coefficient (CLC_LCL​). It is expressed as: CD=CD0+kCL2C_D = C_{D0} + kC_L^2CD​=CD0​+kCL2​ Here, CD0C_{D0}CD0​ is the parasite drag coefficient, and kkk is the coefficient of induced drag. To estimate the drag polar, we need to calculate CD0C_{D0}CD0​ and kkk.  

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