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The induced drag coefficient (CD,i)(C_{D,i})(CD,i) is a dimensionless number that represents the drag due to the generation of lift by a wing or other lifting surface. It is caused by the creation of wingtip vortices and the associated downwash, which increases the effective angle of attack of the wing, reducing its ability to produce lift […]
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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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