# Dr MGR Educational and Research Institute 2009-5th Sem B.Tech Mechanical Engineering Dr.MGR University Gas Dynamics And Jet propulsion mechanical - Question Paper

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B.TECH DEGREE EXAMINATIONS, NOV/DEC - 2009

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BMEE17

CAS DYNAMKj ANj) JET PROPULSION

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Part - A (10x2 = 20 Marks) Answer All Questions

1. State the difference between compressible fluid and incompressible fluid

2. Define Mach Number.

3. Sketch the isentropic and adiabatic expansion process in P-V diagram and T-S diagram.

4. Differentiate nozzle and diffuser.

5. What are the assumptions made for fanno flew?

6. Define fannings coefficient of skin friction.

7. Calculate the strength of shock wave when normal shock appears at M-?.

S. Give the difference between Norma! and oblique shocks.

9. What is monopropellant? Give one example for it

10. Define the terms: 1 .UDMH 2.RFNA 3 JATO 4.RATO. *

Part-S {5x16 = 80 Marks)

Answer AH Questions

i j. Derive an expression fci th .acousjc vsiccity ct oorr piessibe ;fuld flow i;j trnnor its temperature.

(OR)

j 12. A piane travels with a velocity of 1,600 km/hr at an altitude where the pressure and temperature are 40Kpa and -35C. Find the Msch angle and Mach number

< Derive an expression for mass flow iat? n flow through a convergent divergent : nozzle in terms of pressure ratio av] nVdt conditions of the gas. 5

*

Ql a constant area combustion cnsmbsr revives air a, s: ,0.ot> ^{ll} *

the air leaves the combustion chamber st a iv-ach number Of 0 oj, .i-unm. conditions of air end the amount of heat transferred and also find change 1.1 eruropy _{s} J

_{u} , _{irr} t -ires of 0 ' m^{r} and an exft area of 0.44 m . , _{air} riiffuf-er has an mi--! .re.*

/J _{A} cental <* < _{ure ot c} i 8Mos. static temparatura of i

enters the diffuser v.-uh 3 M*. P

and velocity of Z67mft Calcutei? .....

I 7j (a) The m. Aw ^{ra!s o! sv0}'^{jst} *'/7~ ,_{wjr} _{c<} ,h= _{0}-, teq

(b) The mach number. l*mprir a ^{sjr}- ^{c} -

diffuser and _

(c) The net thrust acting acting upon the diussr due to diffuse

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16. Air at an inlet temperature of 60*C flows with subsonic velocity through an insulated _{%} pipe having inside diameter of 50mm and a ienglh of 5m. The pressure at the exit of . the pipe is 101Kpa and the flow is choked the end of the pipe. Sf the friction factor |

4f=0.005.determlne the inlet Macn number, the mass flow rate and the exitjj

. *

temperature. j

TDerive Rankine - Hugoniot equation. j

18. An air jet at a mach number of 2.1 is isentropicaily deflected by 10 in the clockwise \ direction. The initial pressure is 100 KN/m^{2} and initial temperature is 98C.Determine.!

the final state of air after expansion. |

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- 1

C[\_{f} Explain the construction and operation of oolid propellant rocket engine. Ai-^{G nr,,;i}' 4

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f any four solid propellants. |

(OR< J

. .,20. The effective iet velocity from a rocket -s 2700 rn/s. The forward flight vUocty | C WW ._{hrll}*it thrUs.1

1350 m/s and the propellant consumption is 78.fi kg/s. Calculate the m-t |

power and propulsive svitcifcnoy.

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