Aerodynamics Practice Test: Linearized and Conical Flows | Practice Test / Quiz / MCQs

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Aerodynamics Practice Test: Linearized and Conical Flows

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Linearized and Conical Flows topics include: Linearized velocity potential equation, linearized pressure coefficient, linearized subsonic and supersonic flow, critical mach number, conical and supersonic flow physical aspects, quantitative formulation, improved compressibility corrections and historical note. Supersonic linearized conical-flow theory is used to determine the flow over slender pointed cones. The linearized method can have wide application to any form of boundary conditions for conical flow. Conical flow is a flow where physical characteristics like velocity and pressure are... Show more

Linearized and Conical Flows topics include: Linearized velocity potential equation, linearized pressure coefficient, linearized subsonic and supersonic flow, critical mach number, conical and supersonic flow physical aspects, quantitative formulation, improved compressibility corrections and historical note.

Supersonic linearized conical-flow theory is used to determine the flow over slender pointed cones. The linearized method can have wide application to any form of boundary conditions for conical flow.

Conical flow is a flow where physical characteristics like velocity and pressure are constant along each half-ray emerging from a center. Conical flow can play a role in the process of droplet break-up in two and three dimensions.
Conical flow around cones without axial symmetry is analyzed by the superposition of linear conical solutions to a nonlinear axially symmetric conical flow.

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Aerodynamics Practice Test: Linearized and Conical Flows

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1. What does the Prandtl – Glauert rule relate?

Shape of airfoil in transformed spacesIncompressible flow to the compressible flow for same airfoilCoefficient of drag to coefficient of pressureCoefficient of lift to coefficient of pressure

2. The linearized pressure distribution for Mach number greater than 5 matches the coefficient of pressure derived from the exact shock theory.

TrueFalseMaybeDon't know

3. Which equation is used to compute the critical Mach number of the airfoil?

(Cp)crit = γM\(_{crit}^{2} \bigg [ \frac {1 + \frac {1}{2}(γ – 1)}{1 + \frac {1}{2}(γ – 1)M_{crit}^{2}} \bigg ]^{\frac {γ}{γ – 1}}\) – 1(Cp)crit = γM\(_{crit}^{2} \bigg [ \frac {1 + \frac {1}{2}(γ – 1)}{1 + \frac {1}{2}(γ – 1)} \bigg ]^{\frac {γ}{γ – 1}}\) – 1(Cp)crit = \(\frac {2}{γM_{crit}^{2}} \bigg [ \frac {1 + \frac {1}{2}(γ – 1)M_{crit}^{2}}{1 + \frac {1}{2}(γ – 1)} \bigg ]^{\frac {γ}{γ – 1}}\) – 1(Cp)crit = \(\frac {2}{γM_{crit}^{2}} \bigg [ \frac {1 + \frac {1}{2}(γ – 1)M_{crit}^{2}}{1 + \frac {1}{2}(γ – 1)} \bigg ]^{\frac {γ}{γ + 1}}\) + 1

4. For an airfoil kept at supersonic flow, how does the coefficient of pressure vary with an increase in Mach number?

First increases, then decreasesIncreasesDecreasesRemains same

5. Which drag is prominent after exceeding the critical Mach number?

Wave dragSkin – friction dragPressure dragForm drag

6. Linearized velocity potential equation is applicable to hypersonic flow.

MaybeTrueDon't knowFalse

7. The shape of the airfoil in both (x, y) and transformed (ξ, η) space are different.

MaybeTrueFalseDon't know

8. The solution proposed by Taylor and Maccoll for supersonic flow over a cone is obtained using which of these techniques?

NumericallySimulationAnalyticallyGraphically

9. If a cone with half angle 30.2 degrees is kept in a flow at Mach number 3.5, then what is the value of Mach number downstream of the shockwave?

2.4821.1101.6483.45

10. What is the slope of the right running wave characteristic equation?

2au – a2uu + a

11. What is the flow over right circular cone at zero angle of attack is considered to be?

Three – dimensionalQuasi three – dimensionalOne – dimensionalQuasi two – dimensional

12. Which of these is the compatibility equation along C_– characteristic line?

du – \(\frac {dp}{ρa}\) = 0\(\frac {du}{ρa}\) = 0du + \(\frac {dp}{ρa}\) = 0\(\frac {dpu}{ρa}\) = 0

13. How does the coefficient of pressure vary for supersonic flow as the Mach number decreases?

First increases, then decreasesDecreasesIncreasesRemains same

14. Which of these techniques is employed to delay the critical Mach number?

Increase camberIncreasing the thickness of airfoilSwept wingDecrease drag – divergence Mach number

15. How are the streamlines for a conical flow behind a shock wave?

ConicalCurved at the beginning, parallel as surface tends to infinityCurved till surface tends to infinityParallel throughout

16. What is a critical Mach number?

Freestream Mach number for which sonic flow is obtainedFreestream Mach number for which stagnation pressure is obtainedFree stream Mach number for which supersonic flow is obtainedFreestream Mach number for which hypersonic flow is obtained

17. Which of these is the continuity equation for an axisymmetric flow?

\(\frac {1}{r{^2}} \frac {∂}{∂r}\) (r2ρVr) + \(\frac {1}{r sinθ} \frac {∂}{∂θ}\)(ρVθsin⁡θ) + \(\frac {1}{r sinθ} \frac {∂(ρV_ϕ)}{∂ϕ}\) = 02ρVr + ρVθcot⁡θ + ρ\(\frac {∂(V_θ)}{∂θ}\) + Vθ\(\frac {∂(ρ)}{∂θ}\) = 0ρVθcot⁡θ + ρ\(\frac {∂(V_θ)}{∂θ}\) + Vθ\(\frac {∂(ρ)}{∂θ}\) = 02ρVr + ρVθcot⁡θ = 0

18. The numerical solution results in certain amount of truncation error.

FalseMaybeTrueDon't know

19. In which equation is total velocity and it double derivative substituted to obtain the perturbation velocity potential equation?

Perturbation equationMomentum equationVelocity potential equationEnthalpy equation

20. Which of these is the relation for linearized pressure coefficient for two – dimensional bodies?

Cp = \(\frac {2u^{‘}}{V_∞}\) Cp = \(\frac {- 2w}{V_∞}\) Cp = \(\frac {- 2u^{‘}}{V_∞}\) Cp = \(\frac {- 2v^{‘}}{V_∞}\)

21. Where is the application of method of characteristics?

Designing contour of nozzleOptimizing the shape of the fuselageOptimizing the wingDesigning the compressor

22. Which of these assumptions is not made while formulating the linearized supersonic flow?

Thin sharp edged airfoilTwo – dimensional flowLarge camberSmall angle of attack

23. What happens to the flow around the airfoil at upper critical Mach number?

The flow around airfoil becomes subsonicThe flow around airfoil becomes hypersonicThe flow around airfoil becomes supersonicThe flow around airfoil becomes sonic

24. Which of these methods is employed to find solution using method of characteristics?

McLaurin seriesLaurent seriesFourier seriesTaylor series

25. For a thin airfoil kept at a supersonic flow of Mach number 3 at an inclination of 2 degrees, what is the coefficient of pressure?

2.831.780.471.51

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