MCQOPTIONS
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MCQOPTIONS
This section includes 12 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 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 |
| Answer» E. | |
| 2. |
A normal shock wave can be specified with a single velocity. |
| A. | True |
| B. | False |
| Answer» C. | |
| 3. |
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 |
| Answer» C. Downstream temperature | |
| 4. |
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 |
| Answer» D. Thermal and frictional dissipation there | |
| 5. |
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 |
| Answer» B. True | |
| 6. |
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. | \(\frac {\rho_2}{\rho_1}\)=∞ |
| Answer» D. \(\frac {\rho_2}{\rho_1}\)=∞ | |
| 7. |
Which of the following is incorrect for a normal shock wave? |
| A. | M1=1 then M2=1 |
| B. | M1 > then M2 > 1 |
| C. | M\(_1^*\)=1→M\(_2^*\)=1 |
| D. | M1→∞ then M2=finite value |
| Answer» C. M\(_1^*\)=1→M\(_2^*\)=1 | |
| 8. |
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 |
| Answer» C. Mach number, temperature | |
| 9. |
Prandtl relation can also be expressed in terms of characteristic Mach number as 1=M\(_1^*\)M\(_2^*\). |
| A. | True |
| B. | False |
| Answer» B. False | |
| 10. |
Prandtl relation for normal shock waves is_______ |
| A. | a2=u1u2 |
| B. | a*2=u1u2 |
| C. | a*a0=u1u2 |
| D. | a\(_0^2\)=u1u2 |
| Answer» C. a*a0=u1u2 | |
| 11. |
Incompressible flow is a myth actually. |
| A. | True |
| B. | False |
| Answer» B. False | |
| 12. |
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 |
| Answer» B. M > 0.5 | |