Second year, Department of Aeronautical
Engineering
First and second Units Questions.
Answer ALL Questions
PART A – (10 * 2 = 20 Marks)
- Write the steady flow energy equation for an adiabatic flow of air?
- Differentiate between compressible and incompressible flow
- Write the adiabatic relation between temperature, pressure and density.
- Differentiate between static and stagnation temperature?
- Define M* and give the relation between M and M*?
- Define Mach angle and Mach wedge?
- What is chocked flow? State the necessary conditions for this flow to occur in a nozzle?
- Differentiate between shock wave and expansion wave.
- Define Shock angle (β) and Flow deflection angle (θ).
- What is meant by Reflection and Intersection of Shocks and Expansion waves?
PART - B [80 Marks]
11. Derive
all the isentropic relations for one dimensional compressible gas flows. (16)
12. With
neat sketch briefly explain operating performance of Convergent-divergent
nozzle. (16)
13. a.
Derive all the area-Mach number-velocity relation and explain why convergent
divergent nozzle is needed for supersonic flow. (8)
b. Derive the area-Mach number relation for
isentropic flow through variable area duct (8)
14. a)
Derive Prandtl equation and from that prove that the Mach no. behind normal
shock is always less than one (8)
b) Derive the Rankine-Hugonoit pressue density
relationship for the shock and explain its significance. (8)
- With a neat sketch, explain Prandtl-Meyer expansion. Derive an expression for Prandtl-Meyer function. (16)
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