Reg No.:

10000ME409122002 Pages: 3

Name:

APJ ABDUL KALAM TECHNOLOGICAL UNIVERSITY

Seventh Semester B.Tech Degree Regular and Supplementary Examination December 2021 (2015 Scheme)

Course Code: ME409
Course Name: COMPRESSIBLE FLUID FLOW
Max. Marks: 100 Duration: 3 Hours
Use of Gas table is permitted. Assume suitable value for missing data
PARTA

Answer any three full questions, each carries 10 marks. Marks
1 Derive Adiabatic Energy equation applicable to Nozzles/Diffusers (10)
2 A jet of air at 500 K has sonic velocity. Determine (10)
3 ஐ
b)

4
5 2)

i) Velocity of sound at 500 K

ii) Velocity of sound at the stagnation conditions

iii)Maximum Velocity of jet

iv)Stagnation Enthalpy

v)Crocco Number

Take y = 1.4 and R=287 J/kg-K for air.

A gas with y = 1.3 flows through a nozzle. Determine the critical pressure ratio (2)
5

Po
A Nozzle in a wind tunnel gives a test section Mach Number of 2.5. Air enters (8)
the nozzle from a large reservoir at 0.75 bar and 320 K. The cross sectional area
of the throat is 1000cm*. Determine the following for the tunnel for one-
dimensional isentropic flow:
i)pressure, temperature and velocities at throat and test sections
ii) Mass Flow rate
A certain Diffuser has area ratio 3:1. If air (y =1.4, R = 287 J/kg-K) enters the (10)
diffuser with a Mach number of 0.8, pressure of 5 bar and a temperature of 60°C,
compute the exit Mach number, exit velocity, exit temperature, exit pressure and
percentage change in impulse function.
PART 13

Answer any three full questions, each carries 10 marks.

Make a list of flow properties which i) increases, ii) Decreases, iii)Remains (4)

constant across a normal shock

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