The lift coefficient for the airfoil section on a wing ______

Is constant always

Is same for the entire wing

Is equal to the aerodynamic twist

Depends on local lift slope for airfoil

Correct Answer : Depends on local lift slope for airfoil

Explanation : In wings, the lift coefficient for local airfoil section is equal to the local airfoil lift curve slope (2π for thin airfoils) into effective angle of attack minus zero lift angle of attack. Thus, it may or may not be same for the entire wing and is not equal to the aerodynamic twist.

Recently Updated in Aerodynamics Questions

Is loading distribution is represented by the sum of finite number?

True

False

Can Not Say

None of the above

Correct Answer : Option (A) : True

Explanation : In the collocation solution of the basic integral equation, the loading distribution is represented by the sum of a finite number of known functions with unknown coefficient substituting the loading representation into their result.

Is it difficult to predict the analytically overall amount of lift?

True

False

Can Not Say

None of the above

Correct Answer : Option (A) : True

Explanation : It is difficult to predict analytically the overall amount of lift that a wing of given geometry will generate. The lifting line theory yields the lift distribution along the span wise direction based only on the wing geometry and flow conditions.

Is prandtl lifting line theory is a mathematical model that predicts lift distribution over a three-dimensional wing?

True

False

Can Not Say

None of the above

Correct Answer : Option (A) : True

Explanation : The prandtl lifting line theory is a mathematical models that predicts lift distribution over a three dimensional wing based on its geometry. It is also known as the lanchester-prandtl wing theory. It was used to calculate lift on the wing.