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Aerodynamics Practice Test: Compressible Flow through Nozzles, Diffusers and Wind Tunnels
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Avg score: 82% • Most missed: “Which is the Euler’s equation for the quasi – one dimensional flow?”
Compressible flow through nozzles and diffusers is a behavior that occurs when the speed of gas reaches or exceeds the speed of sound. Understanding this behavior is important for the proper design of devices and engines.  Compressible gas jets are used in various energy converting units, such as: Steam and gas turbines Compressor installations Jet and rocket engines Gas ejecting devices  The Schlieren system is a method for testing compressible flow through wind tunnels. It uses a light source projected into a parabolic mirror that reflects the light through the wind tunnel's window.... Show more
Aerodynamics Practice Test: Compressible Flow through Nozzles, Diffusers and Wind Tunnels
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25 Questions

1. What is the relation between the entry and exit entropy of an actual supersonic diffuser?
2. What is the relation between back pressure and exit pressure in case of subsonic flow at the nizzle’s exit?
3. In case of flow inside a nozzle, how should the exit pressure be in relation to the inlet pressure?
4. Which of these conditions is not applicable for choked flow?
5. How is diffuser throat area At2 related to the nozzle throat area At1?
6. Normal shock diffuser is more efficient than the oblique shock diffuser.
7. How is the flow compressed in an ideal supersonic wind tunnel inside a diffuser?
8. What is the role of the diffuser?
9. What is the differential form of energy equation for quasi one – dimensional flow?
10. Why is ideal supersonic diffuser not feasible?
11. What is the differential form of momentum equation for the quasi one – dimensional flow known as?
12. Which of these parameters in quasi – one dimensional flow varies w.r.t. x as opposed to the one – dimensional flow?
13. Which is the Euler’s equation for the quasi – one dimensional flow?
14. What is the ratio of throat area of diffuser to nozzle in supersonic wind tunnel with flow at Mach 2.7?
15. In how many categories is the supersonic wind tunnel classified into?
16. Diffuser is only applicable for incoming subsonic flow.
17. Which of these factors contribute to additional total pressure losses inside the oblique shock diffuser?
18. Normal shock diffuser is less efficient than the oblique shock diffuser.
19. Which of these is not a part of supersonic wind tunnel?
20. Which of these processes is involved in slowing down the air inside the subsonic diffuser?
21. Which of these results in decrease of the flow inside the actual supersonic diffuser?
22. Which nozzle is used in supersonic wind tunnel?
23. For which of these flows do we need a convergent duct to increase the velocity of the flow?
24. What is the diffuser efficiency for hypersonic conditions?
25. What is the relation between the nozzle A1t and diffuser throat area A2t in the supersonic wind tunnel?

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