The correct formula for profile drag coefficient over the finite wing is_______(a) cd=\(\frac {D_f+D_P}{Sq_∞}\)(b) cd=\(\frac {D_P}{Sq_∞}\)(c) cd=\(\frac {D_f}{Sq_∞}\)(d) cd=\(\frac {D_f+D_P+D_i}{Sq_∞}\)The question was asked in an internship interview.The origin of the question is Downwash and Induced Drag topic in division Flow over Airfoils over Finite Wing of Aerodynamics

The correct formula for profile drag coefficient over the finite wing

1.	The correct formula for profile drag coefficient over the finite wing is_______(a) cd=\(\frac {D_f+D_P}{Sq_∞}\)(b) cd=\(\frac {D_P}{Sq_∞}\)(c) cd=\(\frac {D_f}{Sq_∞}\)(d) cd=\(\frac {D_f+D_P+D_i}{Sq_∞}\)The question was asked in an internship interview.The origin of the question is Downwash and Induced Drag topic in division Flow over Airfoils over Finite Wing of Aerodynamics
Answer» Correct choice is (a) CD=\(\frac {D_f+D_P}{Sq_∞}\) The explanation: The profile drag for a wing is the drag CAUSED by viscosity. For moderate ANGLES of attacks, it is same as that for AIRFOILS i.e. a combination of skin- friction drag and pressure drag. The correct formula is cd=\(\frac {D_f+D_P}{Sq_∞}\).

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