Reg No.:

00000ME409121903

Pages: 2

Name:

APJ ABDUL KALAM TECHNOLOGICAL UNIVERSITY

Seventh Semester B.Tech Degree Examination (Regular and Supplementary), December 2020

Max. Marks: 100

b)
3
4
5
6 a)
b)
7 2)

Course Code: ME409
Course Name: COMPRESSIBLE FLUID FLOW

Use of Approved Data Book is Permitted. Assume suitable values for missing data.
PARTA
Answer any three full questions, each carries 10 marks.
Stating suitable assumptions, prove the law of conservation of energy for a
control volume.
Derive adiabatic steady flow elliptic energy equation. Represent various flow
regimes on steady flow adiabatic ellipse.
Show that pressure coefficient in compressible fluids varies as a function of
Mach number.

Explain the effect of Mach number variation on area ratio in subsonic and
supersonic flows and show that for one dimensional isentropic flow

4 = ८5 [1 ४7]
The conditions of air ( = 1.4, Cp = 1.0 kJ/kg) the entry of a nozzle are p = 2bar,
T= 330K and C =145 m/s. If the exit pressure is 1.5 bar, determine for the
isentropic flow the Mach number at entry and exit, flow rate and maximum
possible flow rate. What is the shape of the Nozzle?
PART ‏تا‎

Answer any three full questions, each carries 10 marks.
State and prove Prandtl-Mayer relationship for a normal shock waves.
Can shock waves develop in a subsonic flow? Justify your answer.
Air enters a 30cm diameter duct at a Mach number of 2.5, temperature of 400K
and a pressure of 100kPa. A normal shock wave occurs at a Mach number of 1.7
and the exit Mach number is 0.8. The coefficient of the friction is 0.004.
Calculate the length of duct upstream and downstream of normal shock, change
in entropy and stagnation pressure losses.
Define Fanno flows. Prove that at the point of maximum entropy Mach number

is unity on the Fanno curve.

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Duration: 3 Hours

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