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ME6604 question Bank Gas Dynamics and Jet Propulsion Regulation 2013 Anna University

ME6604 question Bank Gas Dynamics and Jet Propulsion

ME6604 question Bank Gas Dynamics and Jet Propulsion Regulation 2013 Anna University free download. Gas Dynamics and Jet Propulsion question Bank free pdf download.

Sample ME6604 question Bank:

Part A ME6604 question Bank (2 Marks)

1. State the difference between compressible fluid and incompressible fluid ?

2. Define stagnation pressure?

3. Express the stagnation enthalpy in terms of static enthalpy and velocity of flow?

4. Explain Mach cone and Mach angle?

5. Define adiabatic process?

6. Define Mach number?

7. Define zone of action and zone of silence ?

8. Define closed and open system?

9. What is the difference between intensive and extensive properties?

10. Distinguish between Mach wave and normal shock?

Part B ME6604 question Bank (16 Marks)

1.Air is discharged from a reservoir at po = 6.91 bar and to = 325 C through a nozzle to an exit pressure of 0.98 bar. If the flow rate is 3600 Kg/hr, determine throat area, pressure and velocity at the throat, exit area, exit Mach number and maximum velocity. Consider flow is isentropic. (AU: May 2012, Dec 2009, May 2008)

2.A supersonic diffuser diffuses air in an isentropic flow from a mach number of 3 to a mach number of 1.5. The static conditions of air at inlet are 70 kpa and -7 C. If the mass flow nrate of air is 125 kg/s, determine the stagnation conditions, areas at throat and exit, static
conditions (pressure, temperature, velocity) of air at exit. (AU: May 2012)

3.A supersonic nozzle expands air from Po = 25 bar and T0 = 1050 K to an exit pressure of 4.35 bar: the exit are of the nozzle is 100 cm2. Determine i) throat area ii) pressure and temperature at the throat iii) temperature at exit iv) Exit velocity as fraction of the
maximum attainable velocity v) mass flow rate. (AU: May 2011, May 2010)

4.A conical diffuser has entry and exit diameters of 15 cm and 30 cm respectively. The pressure, temperature and velocity of air at entry are 0.69 bar, 340 K and 180 m/s respectively. Determine i) exit pressure ii) the exit velocity and iii) the force exerted on the diffuser walls assume isentropic flow, γ =1.4, Cp = 1.00 J/Kg K (AU: May 2011, May 2010, May 2009 Dec 2008, Dec 2007)

Subject Name Gas Dynamics and Jet Propulsion
Subject Code ME6604
Regulation 2013
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