# FRCR Physics MCQs

Prof. Fazal Rehman Shamil
Solved MCQs of Modern Low-Speed Airfoils in FRCR Physics.

For flow over an airfoil the pressure coefficient distribution is calculated?

(A). True

(B). False

(C). Partially True

Using the numerical technique, NASA airfoil is designed?

(A). False

(B). True

(C). Partially True

The ratio of lift to drag at a lift coefficient is increased by 50%?

(A). True

(B). False

(C). Partially True

The initial distribution is given by solid curves?

(A). True

(B). False

(C). Partially True

Over the top surface of the airfoil at a high angle of attack is flow separation?

(A). True

(B). False

(C). Partially True

NASA LS-0417 airfoil thickness Is 17%?

(A). True

(B). False

(C). Partially True

To verify the computer-designed profiles wind tunnel test is conducted?

(A). True

(B). False

(C). Partially True

To improve the drag at subsonic speed supercritical airfoil is used?

(A). True

(B). False

(C). Partially True

(A). 0.07c

(B). 0.05c

(C). 0.08c

(D). 0.09c

(C). Partially True

Low-speed airfoils are designed by NASA?

(A). True

(B). False

(C). Partially True Prof.Fazal Rehman Shamil (Available for Professional Discussions)