Aircraft Drag Polar
Aircraft parabolic drag polar
- $C_{D0}$, parasite drag coefficient at zero lift.
- , drag coefficient due to lift (induced drag).
- $e$, Oswald efficiency factor, includes all effects from airplane.
- , effective aspect ratio.
- $b_\mathrm{e}=b\sqrt{e}$, effective wing span.
Parabolic polar:
Actual polar:
Generalized parabolic polar
- $C_{L\mspace{2mu}\mathrm{ideal}} = C_L @ C_{D\mspace{2mu} \mathrm{min}}$, ideal lift coefficient, i.e. $C_L$ at the angle of attack of minimum $C_D$.
Equation (\ref{eq:Drag:Polar:Parabolic:B}) is unnecessarily too complicated. An acceptable approximation is given by the simple parabolic drag polar (\ref{eq:Drag:Polar:Parabolic:A}).
Equivalent parassite area
- $C_{f\mspace{2mu}\mathrm{turb}}$, friction coefficient of a flat plate aligned with the flow, calculated in turbulent regime at the aircraft flight Reynolds number $\mathrm{Re} = \rho V \bar{c}/\mu$.
Oswald efficiency factor
(various calculation methods in literature)