coefficient of drag (CD)/drag coefficient

coefficient of drag (CD)/drag coefficient
A coefficient dependent upon the angle of attack, shape of the airfoil, Reynolds number, and Mach number. Drag coefficient (CD ) = Drag (D)/Dynamic Pressure (q) or {1 /2 (Density (ρ) × Air Speed2 (V2 ) × Wing Area (S). CD = D/qS, or 2DV2 S.

Aviation dictionary. 2014.

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