1. Define oblique shock waves

2. Define normal shock waves

3. What are the physical facts of normal shock waves?

4. Write the formulas for calculating normal shock properties.

5. Write the formulas for calculating oblique shock properties.

6. Explain centered expansion wave.

7. Define characteristic mach line.

8. What is meant by pitot static tube .

9. Explain fanno flow.

10. State the property change across oblique shock wave with neat sketch.

11. State the property change across normal shock wave with neat sketch.

12. State the property change across expansion wave.

13. Define expansion waves.

14. State the formulas to calculate velocity in both compressible and incompressible flow.

15. Define mach wave.

16. Define mach angle.

17. Define zone of silence and zone of action.

18. Write the Ɵ-ß-M relation and its uses.

19. What is meant by attached and detached shock wave with diagrams

20. What is meant by left and right running shock wave?

21. Define shock polar.

22. Define hodograph.

23. Define pressure turning angle.

24. Differentiate wedge and cone.

25. Explain Rayleigh flow.

26. Define shock waves.

27. Differentiate shock and expansion waves.

1. a) Derive the relation for prandtl relation for oblique shock waves(8)

b)The diamond shaped wedge angle is 3o, a supersonic air stream of mach number M=2 approaches wedge parallel to the bottom surface. Calculate the lift and drag coefficients. (8)

Or

a) Explain the oblique and normal shock waves with property change across it with neat sketch. Write all formulas related to oblique and normal shock waves.

b) Consider an oblique wave with a wave angle of 30o.The upstream flow mach number is 2.5.Calculate the deflection angle of the flow, pressure, temperature and mach number behind the shock.

2. Consider a supersonic flow with an upstream mach number of 3 and pressure of 1bar.This flow is first expanded around an expansion corner with 15o and then compressed through a compression corner with equal angle of 15o so that it is returned to its original upstream condition. Calculate the mach number and pressure downstream of the compression corner.(12)

A supersonic airplane is flying at mach 2 at an altitude of 16km.After some time ‘t’ how far ahead the airplane? (4)

Or

Consider a mach 3 flow. The flow is slowed by passing through an oblique shock wave with 40o wave angle and then subsequently through a normal shock wave. Calculate the parameters behind the shock wave.(10)

Consider an oblique shock wave with wave angle 35o and pressure ratio of 3.calculate upstream mach number. (6)

3. Derive the relation for rankine- hugonoit relation (8)

A normal shock wave propagates down a constant area duct into stagnant air at a pressure of 100kpa and temperature of 300k.If the pressure ratio across the shock wave is 3, find the shock speed and the velocity of air behind the shock.

Or

Explain the pitot static tube construction and use. Brief the compressibility correction for subsonic incompressible, subsonic compressible and supersonic compressible flow.

4. i)Derive the Ɵ-ß-M relation. Explain attached and detached shock waves.

ii)Explain the effect of increasing the upstream mach number and the effect of increasing the deflection angle.

Or

Consider an infinitely thin flat plate at an angle of attack in mach 2.6 flow. Calculate the lift and drag coefficient for α =15o.Calculate lift and drag coefficients.

6. Derive the relation for prandtl-meyer expansion waves.(16)

8. Explain in detail about Rayleigh and fanno flow with neat sketch.(16)

9. Explain the Method of characteristics in detail with neat sketch.

10. Explain the two dimensional supersonic nozzle contours in detail with neat sketch.

11. Explain shock wave reflection and interactions. Explain detached shock wave in front of a blunt body.

12. Explain shock expansion theory with diamond shaped airfoil and flat plate.

13. i) Why does the isentropic relations are not valid in shocks?

ii) Why does the oblique shocks are preferred over normal shock waves?

iii) Why does the normal shocks are preferred in re-entry bodies?

iv) When does the oblique shock waves turns into normal shock waves?

v)How is the strength of a shock wave determined in a supersonic flow?

vi) Explain why shocks cannot occur in subsonic flows

vii) What happens to the total conditions and entropy across the shock wave?