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→Components of lift and drag coefficients
\[ C_{DI} = \frac{k}{\pi A} C_L^2 \]
Where \( A \) is the aspect ratio of the wings (how slender the wings are), and \( k \) is a factor that depends on the wing design. This drag component increases quadratically with \( C_L \).
By the explanations above, it should be evident that:
\[ C_{D0} = C_{DF} + C_{DP} \]
== Relationship Between Lift and Drag: the Parabolic Polar ==
