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=\(\frac {D_f+D_P}{Sq_∞}\)+DiThe question was posed to me in an interview for internship.My question comes from Downwash and Induced Drag in division Flow over Airfoils over Finite Wing of Aerodynamics

The total drag coefficient for a wing is given by______(a) cd=\(\frac

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=\(\frac {D_f+D_P}{Sq_∞}\)+DiThe question was posed to me in an interview for internship.My question comes from Downwash and Induced Drag in division Flow over Airfoils over Finite Wing of Aerodynamics
Answer» Right choice is (c) Cd=\(\FRAC {D_f+D_P+D_i}{Sq_∞}\) To explain: For wing, the TOTAL drag comprises of viscous drag plus the INDUCED drag. The COEFFICIENT of total drag is given by Cd=\(\frac {D_f+D_P+D_i}{Sq_∞}\), which is NOTHING but Cd=\(\frac {D_f+D_P}{Sq_∞}+\frac {D_i}{Sq_∞}\)i.e. Cd=cd+Cdi.

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