ME6604 Gas Dynamics and Jet propulsion question bank PDF

ANNA UNIVERSITY-CHENNAI

REGULATION 2013

DEPARTMENT OF MECHANICAL ENGINEERING


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ME6604-GAS DYNAMICS AND JET PROPULSION

Unit I – Basic concepts and Isentropic flows

Part A (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 (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 rate 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)

5.4.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)

6.The pressure, temperature and Mach number at the entry of a flow passage are 2.45 bar, 26.5 C and 1.4 respectively. If the exit mach number is 2.5, determine for adiabatic flow of a perfect gas (γ = 1.3, R = 0.469 kJ/Kg K). I) Stagnation temperature. ii) Temperature and velocity of gas at exit. Iii) the flow rate per square metre of the inlet cross-section. (AU: May 2010, May 2008)

7.Air (γ = 1.4, R = 287.43 J/Kg K) enters a straight axis symmetric duct at 300 K, 3.45 bar and 150 m/s and leaves it at 277 k, 2.058 bar and 260 m/s. The area of cross-section at entry is 500cm2. Assuming adiabatic flow determine i) Stagnation temperature ii) maximum velocity iii) Mass flow rate iv) Area of cross section

at exit. (AU: May 2010, May 2008)

8.In an isentropic flow diffuser the inlet area is 0.15 m2. At the inlet velocity 240m/s, static temperature = 300 k and static pressure 0.7 bar. Air leaves he diffuser with a velocity of 120 m/s. Calculate at the exit the mass flow rate, stagnation pressure, stagnation temperature, area and entropy change across the diffuser.

(AU: Dec 2009)

9.Air is drawn isentropically from a standard atmosphere at sea level (101.3 KPa and 15 C) through a converging diverging nozzle. The static pressure at two different locations at 80 KPa and 40 KPa respectively. Determine the Mach number at each of these locations. Also determine the velocity at each of these locations.

(AU: May 2009)

10.Air (Cp = 1.05 KJ/Kg-K, γ = 1.38) at P1 = 3 × 105 N/m2 and T1 = 500 k flows with a velocity of 200 m/s in a 0.3 m diameter duct. Calculate: Mass flow rate, Stagnation temperature, Mach number and stagnation pressure values assuming the flow as compressible and incompressible respectively.

(AU: Dec 2008, Dec 2007)

11.Air flowing in a duct has a velocity of 300 m/s, pressure 1.0 bar and temperature 290 k. Taking γ = 1.4 and R = 287 J/Kg K. Determine: i) Stagnation pressure and temperature. ii) Velocity of sound in the dynamic and stagnation conditions. Iii) Stagnation pressure assuming constant density.

(AU: May 2008, Dec 2007)

12.What is the effect of Mach number on compressibility? Prove for γ=1.4, Po –P / ½ P c² = 1 +¼ M² + 1/40 M 4 + ……. 
(AU: May 2009, Dec 2007, Dec 2006)

13.Derive area ratio as a function of Mach number for one dimensional isentropic flow

(AU: Dec 2008)

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