What will be the location of maximum camber for NACA 13250 with chord – McqOptions

MCQOPTIONS

1.	What will be the location of maximum camber for NACA 13250 with chord length of 2m?
A.	0.32m from leading edge
B.	0.32 from trailing edge
C.	0.32m from trailing edge
D.	0.32 from leading edge
Answer» B. 0.32 from trailing edge

Discussion

No Comment Found

Related MCQs

If I want to locate my minimum pressure at 0.5 of chord c then _____________
Location of aerodynamic centre for low speed airfoil is ____
Determine the corrections or otherwise of the following assertion [A] and reason [R]:Assertion [A]: Most of the wings are using cambered airfoils.
A NACA 22104 airfoil is operating at AOA = 3 . The lift-coefficient at this AOA is 0.15. Determine the value of angle of attack at designed lift co-efficient.
An airfoil is operated with flow velocity such that the pressure on upper and lower surface are 30 Pa and 15 Pa respectively. If chord is 1m then, what will be the lift produced by this airfoil?
The maximum lift co-efficient for NACA 19584 (chord=2.5m) airfoil is____
What will be the location of maximum camber for NACA 13250 with chord length of 2m?
Let s consider we need to design supersonic aircraft then, which type of airfoil should be adopted?
An airfoil is such that the drag produced by airfoil is 25N. Airfoil has chord of 2m and is experiencing dynamic pressure of 10Pa. Find the value of drag co-efficient for airfoil.
Laminar bucket is region where ____