Explore topic-wise MCQs in Aerodynamics.

This section includes 7 Mcqs, each offering curated multiple-choice questions to sharpen your Aerodynamics knowledge and support exam preparation. Choose a topic below to get started.

1.

Mach number independence for conical cylinder is achieved at a lower Mach number compared to the sphere.

A. True
B. False
Answer» C.
Discussion
2.

What happens to the pressure behind an oblique shock wave at very high Mach numbers?

A. p2 = \(\frac {2sin^2 β}{γ + 1}\)
B. p2 = \(\frac {γ – 1}{γ + 1}\)
C. p2 = 1 – \(\frac {2sin^2 β}{γ + 1}\)
D. p2 = \(\frac {2sin 2 β}{γ + 1}\)
Answer» B. p2 = \(\frac {γ – 1}{γ + 1}\)
Discussion
3.

For a flow with Mach number 4, P1 = 2.65 × 104 Pa what is the pressure behind the oblique shock wave having shock angle as 30 degrees?

A. 8.525 × 104 Pa
B. 11.925 × 104 Pa
C. 4.502 × 104 Pa
D. 15.278 × 104 Pa
Answer» C. 4.502 × 104 Pa
Discussion
4.

Boundary condition V.n = 0 is applied at the surface to non dimensionlize the governing equations when fluid is being transferred.

A. True
B. False
Answer» C.
Discussion
5.

Which boundary condition applied at the surface to non dimensionlize the governing equations?

A. V.n = 0
B. V × n = 0
C. V.(V × n) = 0
D. V × (V × n) = 0
Answer» B. V × n = 0
Discussion
6.

Which of these equations represents non – dimensionalize continuity equation?

A. ∂\(\frac {(\overline {ρ} \, \overline {u})}{∂\overline {x}}\) + ∂\(\frac {(\overline {ρ} \, \overline {v})}{∂\overline {y}}\) + ∂\(\frac {(\overline {ρ} \, \overline {w})}{∂\overline {z}}\) = 0
B. ρ u\(\frac {∂ \overline {u}}{∂\overline {x}}\) + ρ u \(\frac {∂ \overline {v}}{∂\overline {y}}\) + ρ u \(\frac {∂ \overline {w}}{∂\overline {z}}\) = 0
C. ρ u\(\frac {∂ \overline {u}}{∂\overline {x}}\) + ρ u \(\frac {∂ \overline {v}}{∂\overline {y}}\) + ρ u \(\frac {∂ \overline {w}}{∂\overline {z}}\) = –\(\frac {∂ \overline {p}}{∂\overline {x}}\)
D. ρ u\(\frac {∂ \overline {u}}{∂\overline {x}}\) + ρ u \(\frac {∂ \overline {v}}{∂\overline {y}}\) + ρ u \(\frac {∂ \overline {w}}{∂\overline {z}}\) = –\(\frac {∂ \overline {p}}{∂y}\)
Answer» B. ρ u\(\frac {∂ \overline {u}}{∂\overline {x}}\) + ρ u \(\frac {∂ \overline {v}}{∂\overline {y}}\) + ρ u \(\frac {∂ \overline {w}}{∂\overline {z}}\) = 0
Discussion
7.

At which flow regime does aerodynamic quantities such as coefficient of pressure, lift become independent of Mach number?

A. Subsonic
B. Supersonic
C. Transonic
D. Hypersonic
Answer» E.
Discussion