Transonic and Hypersonic Flows topics include: Hypersonic flow, mach number independence, hypersonic similarity, hypersonic flow newtonian theory, transonic similarity, murman and cole methods, euler equations and full velocity potential equation solutions. Transonic flow is between Mach 0.8 and 1.2, or about 965 to 1236 km/h (600 to 900 mph). Hypersonic flow is Mach 5 and above, or about 6,150-12,300 (4,000 miles per hour).  Transonic flow is when air flows above, at, and below the speed of sound at the same time at different points on an object. For example, the air on a wing flows... Show more

Transonic and Hypersonic Flows topics include: Hypersonic flow, mach number independence, hypersonic similarity, hypersonic flow newtonian theory, transonic similarity, murman and cole methods, euler equations and full velocity potential equation solutions.

Transonic flow is between Mach 0.8 and 1.2, or about 965 to 1236 km/h (600 to 900 mph). Hypersonic flow is Mach 5 and above, or about 6,150-12,300 (4,000 miles per hour). 

Transonic flow is when air flows above, at, and below the speed of sound at the same time at different points on an object. For example, the air on a wing flows faster, so that air could be supersonic while the air flowing over the body of an airplane could be subsonic. 

Hypersonic flows require other similarity parameters than transonic and compressible flow. 

The governing equations for hypersonic flows include:
Mass conservation
Momentum conservation
Internal energy conservation
Total energy conservation 
 

The source terms for these equations include:
Nitrogen dissociation
Vibrational energy relaxation 

 

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Aerodynamics Practice Test: Transonic and Hypersonic Flows

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25 Questions

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

V.(V × n) = 0V.n = 0V × (V × n) = 0V × n = 0

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

p2 = \(\frac {2sin^2 β}{γ + 1}\) p2 = \(\frac {2sin 2 β}{γ + 1}\) p2 = \(\frac {γ – 1}{γ + 1}\) p2 = 1 – \(\frac {2sin^2 β}{γ + 1}\)

3. On which of these points does the properties of flow field at point A depend?

Point PPoint DPoint BPoint C

4. Two bodies holding hypersonic similarity at small angle of attack need the values of γ and M_∞τ to be same.

FalseTrueMaybeDon't know

5. Why is hypersonic similarity parameter essential?

Hypersonic flow over flat plateHypersonic flow over coneSupersonic flow over wedgesHypersonic flow over slender bodies

6. Which of these equations represents non – dimensionalize continuity equation?

∂\(\frac {(\overline {ρ} \, \overline {u})}{∂\overline {x}}\) + ∂\(\frac {(\overline {ρ} \, \overline {v})}{∂\overline {y}}\) + ∂\(\frac {(\overline {ρ} \, \overline {w})}{∂\overline {z}}\) = 0ρ u\(\frac {∂ \overline {u}}{∂\overline {x}}\) + ρ u \(\frac {∂ \ov

7. The ratio \(\frac {C_p}{τ^{2}}\) behind a shock wave is a function of which of these parameters?

Hypersonic similarity parameter and angle of attackHypersonic similarity parameter K and γAngle of attack and wedge angleCoefficient of lift and wedge angle

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

SubsonicSupersonicTransonicHypersonic

9. For which of these Mach numbers is flow considered to be hypersonic?

M > 51 < M < 5M = 1M < 1

10. How is the shock over a blunt body at hypersonic speed?

ObliqueConicalCurvedDiamond

11. Hypersonic boundary layers grow more rapidly compared to subsonic and supersonic boundary layers.

Don't knowFalseMaybeTrue

12. Disturbances in the case of steady supersonic flow are felt in the entire flow field region.

TrueDon't knowMaybeFalse

13. Which of these surfaces is used for reentry vehicles at hypersonic speed?

CopperAblative surfaceCarbonAluminum

14. Hypersonic similarity is applicable for only irrotational flow.

FalseDon't knowTrueMaybe

15. For which range of values is the hypersonic similarity rule valid for very slender bodies?

2 < K < 1000K > 1.5K = 0.5 to infinity0.5 < K < 1.5

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

TrueDon't knowFalseMaybe

17. What is viscous dissipation?

Loss of potential energy due to viscous effectFrictional dragIncrease in kinetic energy due to increase in temperatureLoss of kinetic energy due to viscous effect

18. What is the detrimental effect of high temperature hypersonic flow over a vehicle?

Altitude problemCommunication blackoutFriction causing depletion of ablationAttitude problem

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

Don't knowTrueMaybeFalse

20. Which of these does not result in two or more flows being dynamically similar?

Non dimensional parameters remain sameStreamlines are geometrically similarThe shape of the blunt body is sameLength of the body is same

21. In which region will the disturbances be felt in a steady supersonic flow?

Point C onlyPoint A onlyPoint C and DPoint A and B

22. 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?

15.278 × 104 Pa4.502 × 104 Pa11.925 × 104 Pa8.525 × 104 Pa

23. What is viscous interaction?

Interaction between shock wave and inviscid flowInteraction between shock wave and viscous flow inside boundary layerInteraction between viscous flow and boundary layerInteraction between inviscid flow and boundary layer

24. How is the shock layer in case of hypersonic flow?

Increases with increasing Mach numberNon existentThickThin

25. For a point in the supersonic flow lying at the intersection of the characteristics, its flow field properties depend on change in which of these regions?

Region outside the characteristicsIntersection points of the characteristicsDomain of dependenceRegion of influence