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Select the incorrect equation for the induced drag coefficient for a finite wing.(a) CD,i=\(\frac {C_l^2}{\pi AR}\)(1+δ)(b) CD,i=\(\frac {C_l^2}{\pi AR}\)(c) CD,i=\(\frac {C_l^2s}{\pi eb^2 }\)(d) CD,i=\(\frac {C_l^2}{\pi eAR}\)I had been asked this question in a job interview.I need to ask this question from Prandtl’s Classical Lifting-Line Theory in portion Flow over Airfoils over Finite Wing of Aerodynamics |
Answer» Correct option is (b) CD,i=\(\frac {C_l^2}{\pi AR}\) |
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