05-10-2012, 01:03 PM
GAS DYNAMICS AND JET PROPULSION MODEL QUESTION PAPER
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PART A (10x2=20)
1) Explain Mach cone and Mach angle?
2) Define zone of action and zone of silence ?
3) What is Impulse function ?
4) What is chocked flow through a nozzle?
5) What is Rayleigh line and Fanno line?
6) Explain chocking in Fanno flow?
7) State the necessary conditions for a normal shock to occur in compressible flow?
8) Shock waves cannot develop in subsonic flow? Why?
9) What is specify impulse of rocket?
10) Define propulsive efficiency?
PART B (5X16=80)
11(a) An aircraft flies at 800 Km/hr at an altitude of 10,000 meters (T=223.15 K,P=0.264 bar). The air is reversibly compressed in an inlet diffuser. If the Mach number at the exit of the diffuser is 0.36 determine (a) entry Mach number and (b) velocity, pressure and temperature of air at diffuser exit.
OR
(b) Air (Cp =1.05 KJ/Kg K,γ =1.38) at p1 =3*10 ^5 N/m² and T1 =500 k flows with a velocity of
200 m/s in a 30 cm diameter duct. Calculate mass flow rate,stagnation temperature,Mach number, and,Stagnation pressure values assuming the flow as compressible and incompressible.
12(a)A nozzle in a wind tunnel gives a test –section Mach number of 2.0 .Air enters the nozzle from a large reservoir at 0.69 bar and 310 k .The cross –sectional area of the throat is 1000cm².Determine the following quantites for the tunnel for one dimensional isentropic flow
1) Pressures,temperature and velocities at the throat and test sections,
2) Area of cross- sectional of the test section ,
3) Mass flow rate,
4) Power rate required to drive the compressor.
OR
(b)Air is discharged from a reservoir at Po =6.91bar and To =325˚c through a nozzle to an exit pressure of 0.98 bar .If the flow rate is 3600Kg/hr determine for isentropic flow:
1)Throat area, pressure,and velocity,
2)Exit area,Mach number ,and
3)Maximum velocity.