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 $k$ is the coefficient of induced drag. To estimate the drag polar, we need to calculate CD0C_{D0}CD0​ and $k$.