Define stalling angle in the graph.

The curve remains constant at all section

Lift curve will increases and drag curve will remain constant

The curve increases at different section and decreases rapidly at different section

The curve increases maximum at a particular section and decreases rapidly in the same section

Correct Answer : The curve increases maximum at a particular section and decreases rapidly in the same section

Explanation : The lift curve reaches its maximum for any wing section at certain degree of angle of attack and then rapidly decreases at some degree of angle of attack is therefore the stalling angle. Stalling will occurs at particular degree were the maximum lift will be achieved by the aircraft at that point stalling will takes place.

Recently Updated in Aerodynamics Questions

Is laminar flow is used to increase the drag and reduce the lift?

True

False

Can Not Say

None of the above

Correct Answer : Option (A) : True

Explanation : The effect can also be exploited by devices such as aerodynamic spoilers on aircraft, which deliberately spoil the laminar flow to increase the drag and reduce the lift on the aircraft, which also used as a break to stop the aircraft

Example of turbulent flow?

Laminar flow

Flow on a symmetric airfoil

Smoking rises from cigarette

Turbulent flow on the airfoil

Correct Answer : Option (C) : Smoking rises from cigarette

Explanation : Smoke rising from a cigarette is mostly turbulent flow. However, for the first few centimeters, the flow is laminar. The smoke plume becomes turbulent as its Reynolds number increases, due to its flow velocity and the characteristic length.

Is lift is generated due to large pressure gradients on the upper side of the airfoil?

True

False

Can Not Say

None of the above

Correct Answer : Option (A) : True

Explanation : At higher angles, very large adverse pressure gradients that develop on the upper side as the airfoil attempts to generate more lift causes the boundary layer to separate, leading to a major disruption of the flow over the airfoil and the wing stalls.