The value of integral ∫\(_0^?\frac {cos⁡n\theta d\theta }{cos⁡\ – McqOptions

MCQOPTIONS

1.	The value of integral ∫\(_0^?\frac {cos⁡n\theta d\theta }{cos⁡\theta-cos∅}\)=π\(\frac {sin⁡ n∅}{sin ⁡∅}\) is valid for the limit 0 to_____
A.	π
B.	2π
C.	–π
D.	nπ
Answer» B. 2π

Discussion

No Comment Found

Related MCQs

Which of the following is not correct for symmetric airfoil according to the fundamental equation of thin airfoil in transformed coordinates?
The Kutta Condition according to the thin airfoil theory is_____
The value of integral ∫\(_0^?\frac {cos⁡n\theta d\theta }{cos⁡\theta-cos∅}\)=π\(\frac {sin⁡ n∅}{sin ⁡∅}\) is valid for the limit 0 to_____
Identify ‘a’ as shown in the figure for a thin airfoil.
The fundamental equation for the thin airfoil theory does not encompass which of the following approximations?
The following equation is known as_________Equation: \(\frac {1}{2\pi }\int_0^c \frac {\gamma (\xi)d\xi }{(x-\xi)}\)=V∞(α-\(\frac {dz}{dx}\))(Where c is the chord length for a thin airfoil, α is the angle of attack, V∞ is the free-stream velocity, \(\frac {dz}{dx}\) is the slope at point x and γ(x) is the vortex strength at x).
Which is the component of free-stream velocity normal to the camber line for the given thin airfoil?
Find the induced velocity in the direction normal to the camber line a point on where the slope is 0.087. Given the angle of attack is 5° and free-stream velocity is 20 units. Use thin airfoil approximation.
Identify the missing angle given by the question mark for the following camber distribution of a thin airfoil.
The thin airfoil theory assumes the vortex sheet is kept along the chord line and the camber line acts as a__________