This set of Aerodynamics Multiple Choice Questions & Answers (MCQs) focuses on “Flow Compressible”.

1. The definition of flow being compressible is______

a) M > 0.3

b) M > 0.5

c) Depends on precision required

d) Another name for supersonic flows

View Answer

Explanation: For the subsonic flows, it depends on the matter of accuracy whether to treat a flow as compressible or not. For supersonic flows it is always compressible. In general, M > 0.3 can be regarded as compressible flow.

2. Incompressible flow is a myth actually.

a) True

b) False

View Answer

Explanation: Strictly speaking, all flows are compressible i.e. incompressible flow is a myth actually. But for all practical applications, flow with Mach number < 0.3 can be assumed incompressible since the density variation is less than 5%.

3. Prandtl relation for normal shock waves is_______

a) a^{2}=u_{1}u_{2}

b) a^{*2}=u_{1}u_{2}

c) a*a_{0}=u_{1}u_{2}

d) a\(_0^2\)=u_{1}u_{2}

View Answer

Explanation: The Prandtl relation for the normal shock waves taking into account combined form of mass and moment equation and alternate forms of the energy equation. The final equation comes out in the form of a

^{*2}=u

_{1}u

_{2}, where u

_{1}, u

_{2}are velocities before and after the normal shock.

4. Prandtl relation can also be expressed in terms of characteristic Mach number as 1=M\(_1^*\)M\(_2^*\).

a) True

b) False

View Answer

Explanation: The Prandtl relation is given as a

^{*2}=u

_{1}u

_{2}while the characteristic Mach number is given as M*=\(\frac {u}{a^{*}}\). So, putting this into the Prandtl relation we get the equation 1=M\(_1^*\)M\(_2^*\) where M\(_1^*\) and M\(_2^*\) are the characteristic Mach number upstream and downstream of the normal shock.

5. For a particular gas, Mach number behind the shock wave is a function of which all parameters ahead of the shock wave. Choose the correct option.

a) Mach number, pressure

b) Mach number only

c) Mach number, temperature

d) Mach number, temperature, pressure

View Answer

Explanation: The remarkable result for the normal shock wave is that for a given gas (given gamma), the Mach number ahead of the normal shock wave is a function of the Mach number ahead of the normal shock wave only, irrespective of pressure, density, temperature etc. The values are tabulated and found in gas tables for reference.

6. Which of the following is incorrect for a normal shock wave?

a) M_{1}=1 then M_{2}=1

b) M_{1} > then M_{2} > 1

c) M\(_1^*\)=1→M\(_2^*\)=1

d) M_{1}→∞ then M_{2}=finite value

View Answer

Explanation: For a normal shock wave, the upstream and downstream Mach numbers are related irrespective of the other parameters for a particular flow. According to the relation, M

_{1}=1 then M

_{2}=1 and M

_{1}> then M

_{2}< 1, since normal shock wave compresses the flow. Also, by Prandtl relation when M\(_1^*\)=1→M\(_2^*\)=1 and when M

_{1}→∞ then M

_{2}takes a finite value.

7. Select the correct statement for a Mach wave.

a) M > 1

b) \(\frac {P_2}{P_1}\)=0.528

c) \(\frac {T_2}{T_1}\)=1

d) \(\frac {\rho_2}{\rho_1}\)=∞

View Answer

Explanation: A Mach wave is a normal shock wave of diminishing strength. It occurs for M=1 upstream. Then downstream M=1 also. And all the ratios are equal to 1, i.e \(\frac {P_2}{P_1}\)=1, \(\frac {T_2}{T_1}\)=1, \(\frac {\rho_2}{\rho_1}\)=1. This can be found by calculation when we put m=1. The properties across Mach wave do not change.

8. Shock waves can occur both in subsonic and supersonic medium since the concerning equations are not concerned with whether M > 1 or M < 1.

a) False

b) True

View Answer

Explanation: Equations of mass, momentum, energy are valid in both super and subsonic mediums and hence shock wave can occur in both mediums. But, thermodynamics delete the possibility of shockwaves occurring in subsonic medium. Entropy change is negative if the upstream medium is subsonic and hence no shock waves occur in subsonic medium, else second law is violated.

9. Select the false statement for the normal shock wave.

a) Entropy increases across normal shock wave

b) Normal shock wave has velocity and pressure gradients

c) Shock wave is pretty thick

d) Thermal and frictional dissipation there

View Answer

Explanation: The shock waves are a very thin region and have entropy increase across them. The normal shock wave has large velocity and temperature gradients across it and hence the irreversibility. The thermal conduction and frictional effect lead to increase in entropy.

10. Specifying the temperature ratio across the normal shock wave will yield which of the following across the normal shock wave?

a) Upstream flow velocity

b) Upstream Mach number

c) Downstream temperature

d) Downstream flow velocity

View Answer

Explanation: Specifying a dimensionless quantity across the normal shock wave will specify all the other ratios and both the upstream and downstream Mach numbers. But for finding the velocity, temperature also needs to be specified and vice versa.

11. A normal shock wave can be specified with a single velocity.

a) True

b) False

View Answer

Explanation: When the single velocity is given, either upstream or downstream, a host of various temperatures will give a set of various Mach numbers, and hence different normal shock waves. But if the temperature is given along with the velocity, both either upstream or downstream, it specifies the normal shock wave.

12. The total temperature across the normal shock wave is constant. Which statement gives the wrong reason for this?

a) Adiabatic flow across normal shock wave

b) Normal shock wave has an isentropic flow

c) Calorifically perfect gas

d) Thermal dissipation there

View Answer

Explanation: The flow across the normal shock wave is isentropic i.e. it is adiabatic also. Since, we are concerned with calorically perfect gases in an adiabatic, inviscid, steady flow the total temperature remains constant. Thermal dissipation is not a reason for total temperature being constant.

13. Select the false statement for the normal shock wave.

a) Entropy increases across normal shock wave

b) The total pressure remains constant

c) The total temperature remains constant

d) Normal shock wave is a compression wave

View Answer

Explanation: Across the normal shock wave, the entropy increases, by second law of thermodynamics. It is a compression wave and the total pressure also changes. It is related to the entropy change inversely. Also, being an adiabatic flow, total temperature remains constant.

**Sanfoundry Global Education & Learning Series – Aerodynamics**.

To practice all areas of Aerodynamics, __here is complete set of 1000+ Multiple Choice Questions and Answers__.

**If you find a mistake in question / option / answer, kindly take a screenshot and email to [email protected]**

**Related Posts:**

- Practice Aerospace Engineering MCQs
- Check Aeronautical Engineering Books
- Practice Aeronautical Engineering MCQs
- Apply for Aerospace Engineering Internship
- Check Aerospace Engineering Books