Rajasthan Technical University 2010 B.Tech Mechanical Engineering Fundamentals of Aerodynamics - Question Paper

byOxygen enters die converging section and a normal shock occurs at die exit.

The entering mch number is 2.7.and the area ratio 4/4 =1-7. Compute the overall static temperature ratio T/T,. Neglectall frictional losses [r= 1.4].

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SE3177

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3.    a) Define the following:    (2x2=4)

i)    Mach angle

ii)    Mach number

M Air enters isentropic diffusers with a Mach number of 3.6 and is decelerated

* to a mach number of 2. The diffuser passes a flow of 15kg/s. The initial static pressure and temperature of the air are 1.05 bar and 40C. Assuming r -1,4,Calculate area,total pressure and total temperature at inlet and exit and static temperature and pressure at exit.    (12)

OR

a) What do you mean by choked flow. Discuss about the flow through convergent divergent nozzles?    (8)

bV'¹ Air flow in an adiabatic duct without friction. At one section the Mach number is 1.5 and farther downstream it has increased to 2.8. Find the area ratio, (taker =1.4).    (8)

Unit-IV

4.    a) /What do you mean by adiabatic flow. What is the use of fanno line tables? A

(6V

by Air at p₈ - 10 bar, T₀ = 400 K. isjsypplied to a SO mm diameter pipe. The friction factor for the pipe surface is 0.002. If the mach number changes from 3.0 at the entry to 1.0 at the exit, determine the length of the pipe [r-1.4]    (10)

OR

a)    Discuss the phenomena of chocking due to friction. What is a Diabatic low?

(6)

b)    A constant area combustion chamber is supplied air at 1.2 bar and mach number 1.5, at exit the mach number changes to 3.0, determine exit pressure and the dinotian of beat transfer. [r=1.4].    (10)

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5.    a) Discuss about plane stationary normal shock?    (8)

b) Discuss in detail, Ranking - Huganiot relations?    (8)

OR .

a)/y/bat are prandtls relations?    (4