List of top Aerodynamics Questions on Airfoils and Wings

For an airfoil section the pitching moment coefficient is determined about a reference point that is 0.3 times the chord behind the leading edge. It varies with the lift coefficient as shown in the table below. The distance of the aerodynamic center from the leading edge of the airfoil as a fraction of the chord is ________ (rounded off to one decimal place).

\(c_l\)	0.2	0.4	0.6	0.8
\(c_m\)	-0.02	0	0.02	0.04

Shown below are qualitative illustrations of the lift curve for an airfoil when two different control surfaces are in their respective retracted and deployed configurations. Which of the following is/are TRUE?

Thin airfoil theory predicts the zero-lift angle of attack \(\alpha_{L=0}\) of NACA 2412 airfoil as \(-2.1^{\circ}\). The corresponding prediction of \(\alpha_{L=0}\) for NACA 5410 airfoil is _______ degrees (rounded off to 1 decimal place).

The fundamental purpose of the Kutta condition in the thin airfoil theory is .

Consider a conventional subsonic fixed-wing airplane. \(e\) is the Oswald efficiency factor and \(AR\) is the aspect ratio. Corresponding to the minimum \(\left(\frac{C_D}{C_L^{3/2}}\right)\), which of the following relations is true?

NACA 2412 airfoil has

A finite wing of elliptic planform with aspect ratio 10 and symmetric airfoil operates at \(5^\circ\) angle of attack in uniform flow. The induced drag coefficient is \(\underline{\hspace{1cm}}\) (round off to three decimal places).

Which of the following statement(s) is/are true with regards to Kutta condition for flow past airfoils?