Answer All The Questions (10 2 20)
Answer All The Questions (10 2 20)
Answer All The Questions (10 2 20)
No : AD/05
SCHOOL OF ENGINEERING AND TECHNOLOGY Date : 03-02-2015
Department: Mechanical Engg. Title: INTERNAL TEST I Page. No : 1 of 1
Class : II Mech
Subject : GDJP Max.Marks : 100
Semester : VI Time : 3 hrs
4. Air ( =1.4 , R= 287.43 j/kg-k) enters a straight axisymmetric duct at 300k , 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 500 cm2. Assuming adiabatic flow determine :
(I) Stagnation temperature
(II) Maximum velocity
(III) Mass fow rate, and
(IV) Area of cross-section at exit.
5. Air (cp = 1.05 kj/kg-k,=1.38) at p1= 3x 105 N/m2 and T1=500 k flows with a
velocity of 200 m/s in a 30 cm diameter duct. Calculate :
(a) Mach number (b) stagnation temperature (c) mass flow rate (d) stagnation
pressure values assuming the flow as compressible and incompressible.
6. An aircraft is flying at an altitude of 12000 meters (T=216.65k,p=0.193bar) at a
Mach number of 0.82. the cross sectional area of the inlet diffuser before the LP
compressor stage is 0.5m3. determine
1) The mass of air entering the compressor per second
2) The speed of the sircraft
3) The stagnation pressure and temperature of air at the siffusr entry
8. Air flowing in a duct has a velocity of 300m/s, pressure 1.0bar and temperature
290k. taking =1.5 R=287J/Kg-K determine
1) Stagnation pressure and temperature
2) Velocity of sound in the dynamic and stagnation conditions
3) Stagnation pressure assuming constant density