Explore topic-wise MCQs in Aerodynamics.

This section includes 13 Mcqs, each offering curated multiple-choice questions to sharpen your Aerodynamics knowledge and support exam preparation. Choose a topic below to get started.

1.

The lift per unit span for a thin, cambered airfoil with =10 ( frac {m^2}{s} ), =1.0255 ( frac {kg}{m^3} ), V =10 ( frac {m}{s} ) is____

A. 0
B. 102.55 ( frac {N}{m} )
C. 102.55N
D. 55 ( frac {N}{m} )
Answer» B. 102.55 ( frac {N}{m} )
Discussion
2.

The lift per unit span for a thin, cambered airfoil with =5 , A0=0.65, A1=1 is____

A. L = c (V_ ^2 ) <sub> </sub> (1.15)
B. L = c (V_ ^2 ) <sub> </sub> (1.65)
C. L = c (V_ ^2 ) <sub> </sub> (-0.35)
D. L = c (V_ ^2 ) <sub> </sub> (0.15)
Answer» B. L = c (V_ ^2 ) <sub> </sub> (1.65)
Discussion
3.

For =5 , A0=1 and A1=-2 total circulation for a thin cambered airfoil equals______

A. 0
B. 2 cV<sub> </sub>
C. cV<sub> </sub>
D. 2.5 cV<sub> </sub>
Answer» B. 2 cV<sub> </sub>
Discussion
4.

The correct formula for the Fourier sine series appearing in the solution of thin airfoil theory is_____

A. A<sub>n</sub>= ( frac {2}{ pi } int_0^{ pi } frac {dz}{dx} ) cos u2061n d
B. A<sub>n</sub>= ( frac {1}{ pi } int_0^{ pi } frac {dz}{dx} ) cos u2061n d
C. A<sub>n</sub>= ( frac {2}{ pi } int_0^{2 pi } frac {dz}{dx} ) cos u2061n d
D. A<sub>n</sub>= - ( frac {1}{ pi } int_0^{ pi } frac {dz}{dx} ) cos u2061n d
Answer» B. A<sub>n</sub>= ( frac {1}{ pi } int_0^{ pi } frac {dz}{dx} ) cos u2061n d
Discussion
5.

For ( )=2V (A0 ( frac {1+cos theta }{sin theta } ) + (_{n=1}^ )sin n An) select the statement which is invalid.

A. The solution is valid only for cambered airfoils
B. The solution is valid for all thin airfoils
C. A<sub>0</sub> Is the n=0<sup>th</sup> term for the Fourier series
D. Kutta condition is satisfied at the trailing edge i.e. = .
Answer» B. The solution is valid for all thin airfoils
Discussion
6.

Select the statement which is not true for the solution of ( frac {1}{2 pi } int_0^c frac { gamma( xi)d xi}{x- xi} )=V ( - ( frac {dz}{dx} )) for a cambered airfoil.

A. A<sub>n</sub> depends on chord length of the airfoil
B. A<sub>0</sub> depends on the slope of the camber line
C. A<sub>n</sub> depends on the slope of the camber line
D. A<sub>0</sub> depends on the angle of attack
Answer» B. A<sub>0</sub> depends on the slope of the camber line
Discussion
7.

For an angle of attack of 5 and slope of camber line being zero, find the value of A0.

A. 0.087
B. 5
C. 0
D. -5
Answer» B. 5
Discussion
8.

NACA 0023 is______

A. Negatively cambered airfoil
B. Positively cambered airfoil
C. Symmetrical airfoil
D. Thin cambered airfoil
Answer» D. Thin cambered airfoil
Discussion
9.

For NACA4313 what is the maximum camber and the position of maximum camber from the leading edge respectively is______

A. 0.04c, 0.4c
B. 0.4c, 0.03c
C. 0.13c, 0.4c
D. 0.04c, 0.03c
Answer» B. 0.4c, 0.03c
Discussion
10.

The extra term appearing in the thin airfoil theory solution for a cambered airfoil is a______

A. Full Fourier series
B. Fourier sine series
C. Fourier cosine series
D. Constant
Answer» C. Fourier cosine series
Discussion
11.

The equation ( frac {1}{2 pi } int_0^c frac { gamma( xi)d xi}{x- xi} )=V is called the fundamental equation of thin airfoil theory for______

A. Cambered airfoils only
B. Symmetric airfoils only
C. All thin airfoils
D. Symmetric and positively cambered airfoils
Answer» C. All thin airfoils
Discussion
12.

Which of the following is incorrect for a thin, cambered airfoil?

A. The angle of attack is small
B. The induced velocity distribution for the camber line is the same for the chord line
C. Vortex sheet is kept at the chord line
D. The slope of the camber line is zero
Answer» E.
Discussion
13.

The camber line is not a streamline of flow for a cambered airfoil according to the thin airfoil theory.

A. Always true
B. Always false
C. True only for thin airfoils
D. Depends on the camber distribution
Answer» C. True only for thin airfoils
Discussion