Home > Aircraft & Aviation > Quizzes > Aerodynamics Practice Test: Normal Shock Waves
Aerodynamics Practice Test: Normal Shock Waves
Fast practice, instant feedback. Timer auto-submits when time’s up.
Avg score: 82% Most missed: “The characteristic Mach number and Mach number are related. Which of these is no…”
Normal Shock Waves topics include: Normal shock equations, flow compressible and its velocity measurement. A normal shock wave is a one-dimensional flow configuration that can be used to study flow behavior and transport processes.  A normal shock wave is a shock with a wave front that is perpendicular to the freestream flow. They occur in supersonic internal and jet flows.  A normal shock wave is the most fundamental type of shock. It is a traveling wave that moves relative to the fluid faster than the local speed of sound.  Here are some characteristics of normal shock waves: Shock... Show more
Aerodynamics Practice Test: Normal Shock Waves
Time left 00:00
25 Questions

1. The characteristic Mach number and Mach number are related. Which of these is not correct?
2. The characteristic Mach number is constant for a given value of temperature and gamma.
3. For a non-perfect gas, if we double the pressure while keeping the temperature same, the speed of sound remains the same.
4. .The properties of a flow with subscript * denotes M=1. Which of these is the correct ratio for a flow with gamma= 1.4?"
5. The fundamental expression for the speed of sound in a gas is not given by which of the following equations?
6. The most important quantity that dominates the physical properties of compressible flow is _______
7. The incorrect relation for properties associated with the flow, for a point in the flow where the speed of sound is a, is_______
8. Which of these is incorrect for the normal shock wave analysis?
9. The speed of sound in any medium is a function of_____
10. The incorrect equation for the normal shock equation is_______
11. Incompressible flow is a myth actually.
12. Select the false statement for the normal shock wave.
13. The definition of flow being compressible is______
14. The correct statement for a point where the speed of sound is a, is_______
15. Select the correct statement for a Mach wave.
16. Mach number is a measure of the directed motion of the gas compared with the random thermal motion of the molecules.
17. For a perfect gas, if we half the density, keeping the temperature same the speed of sound changes. This is due to the change in pressure.
18. Prandtl relation for normal shock waves is_______
19. Which of the following is incorrect for a normal shock wave?
20. 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.
21. A normal shock wave can be specified with a single velocity.
22. For supersonic compression flows, there is a bow shock formed at the mouth of the Pitot tube.
23. Shock waves can occur both in subsonic and supersonic medium since the concerning equations are not concerned with whether M > 1 or M < 1.
24. The isentropic compressibility, in terms of speed of sound in any medium is given by ________
25. The total temperature across the normal shock wave is constant. Which statement gives the wrong reason for this?