MCQOPTIONS
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MCQOPTIONS
| 1. |
The total drag coefficient for a wing is given by______ |
| A. | cd=\(\frac {D_f+D_P+D_i}{Sq_∞}\) |
| B. | Cd=\(\frac {D_f+D_P}{Sq_∞}\) |
| C. | Cd=\(\frac {D_f+D_P+D_i}{Sq_∞}\) |
| D. | Cd=\(\frac {D_f+D_P}{Sq_∞}\)+Di |
| Answer» D. Cd=\(\frac {D_f+D_P}{Sq_∞}\)+Di | |