A symmetric airfoil is operating with flow velocity of 350m/s. The li – McqOptions

MCQOPTIONS

1.	A symmetric airfoil is operating with flow velocity of 350m/s. The lift produced by the airfoil is 21 N at 0.008 rad AOA. If chord is c m then, what will be the pressure difference across the airfoil?
A.	21/c Pa
B.	21c/2 N
C.	21 Pa
D.	21c N
Answer» B. 21c/2 N

Discussion

No Comment Found

Related MCQs

We are using the airfoil in the aircraft as _____
Which of these is not part of an airfoil?
Pitching moment co-efficient for an airfoil is given by _____
An airfoil is subjected to the flow with temperature of 288.16K and flow is ideal. The velocity at the leading edge is ____
Consider a NACA 2812 airfoil. It is operating with flow velocity of 900m/s with chord of 1m. What should be the maximum thickness of this airfoil?
Find location of aerodynamic centre from leading edge if, chord is 10m and airfoil has flow velocity of 0.2 M.
If an airfoil has lift of 200 N at 10° AOA, then what is induced drag produced by airfoil at that AOA?
A symmetric airfoil is operating with flow velocity of 350m/s. The lift produced by the airfoil is 21 N at 0.008 rad AOA. If chord is c m then, what will be the pressure difference across the airfoil?
Airfoil is a streamline shape.
Which of the following is not type of an airfoil?