MCQOPTIONS
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MCQOPTIONS
This section includes 10 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 is a measure of the directed motion of the gas compared with the random thermal motion of the molecules. |
| A. | False |
| B. | True |
| Answer» C. | |
| 2. |
The isentropic compressibility, in terms of speed of sound in any medium is given by ________ |
| A. | <sub>s</sub>= a<sup>2</sup> |
| B. | <sub>s</sub>= ( frac {1}{ rho a^2} ) |
| C. | <sub>s</sub>= ( frac { rho }{a^2} ) |
| D. | <sub>s</sub>= ( frac {1}{ rho a} ) |
| Answer» C. <sub>s</sub>= ( frac { rho }{a^2} ) | |
| 3. |
The speed of sound in any medium is a function of_____ |
| A. | P, |
| B. | P, T |
| C. | T only |
| D. | T, |
| Answer» D. T, | |
| 4. |
The fundamental expression for the speed of sound in a gas is not given by which of the following equations? |
| A. | a<sup>2</sup>= ( frac {dp}{d rho } ) |
| B. | a= ( sqrt {( frac { partial p}{ partial rho })s} ) |
| C. | a= ( sqrt { frac { gamma p}{ rho }} ) |
| D. | a= ( sqrt { gamma ^2RT} ) |
| Answer» E. | |
| 5. |
The equation a=- ( frac {da}{d rho } ) where a is the speed of sound in the medium is the mathematical expression derived for the sound waves, which are _________ |
| A. | Isentropic |
| B. | Incompressible |
| C. | Adiabatic |
| D. | Reversible |
| Answer» B. Incompressible | |
| 6. |
The most important quantity that dominates the physical properties of compressible flow is _______ |
| A. | Speed of sound |
| B. | Speed of light |
| C. | Density of medium of propagation |
| D. | Distance of propagation |
| Answer» B. Speed of light | |
| 7. |
The incorrect equation for the normal shock equation is_______ |
| A. | <sub>1</sub>u<sub>1</sub>= <sub>2</sub>u<sub>2</sub> |
| B. | p<sub>1</sub>+ <sub>1</sub>u (_1^2 )=p<sub>2</sub>+ <sub>2</sub>u (_2^2 ) |
| C. | h<sub>1</sub>+ ( frac {u_1^2}{2} )=h<sub>2</sub>+ ( frac {u_2^2}{2} ) |
| D. | .v=0 |
| Answer» E. | |
| 8. |
Which is not true for continuity equation of normal shock? |
| A. | <sub>1</sub>u<sub>1</sub>A<sub>1</sub>= <sub>2</sub>u<sub>2</sub>A<sub>2</sub> |
| B. | <sub>1</sub>u<sub>1</sub>= <sub>2</sub>u<sub>2</sub> |
| C. | Steady flow |
| D. | No viscosity |
| Answer» C. Steady flow | |
| 9. |
Which of these is incorrect for the normal shock wave analysis? |
| A. | No viscous effects or body forces |
| B. | Adiabatic flow |
| C. | Differential form of conservation equations used |
| D. | Steady flow |
| Answer» D. Steady flow | |
| 10. |
A shock wave that is normal to the upstream flow is a rare case. |
| A. | False |
| B. | True |
| Answer» B. True | |