25 The air stream passes U0 shock wave that is generated by

2.5. The air stream passes U0 shock wave that is generated by the wedge is retlell Find the pressure and Mach number after the reflection. 15. Air at a pressure and temperature of 40 kPa and -30°C flows at Mach 3 down a leading wide duct. The upper wall of the duct turns sharply through an angle of 5 5° M 3 \"Reflected\" shock p3 Pi = 40 kPa T1 =-30°C 2° RE P6.15 situation considered.

Solution

mach number is the ratio f flow velocity to velocity of sound in medium

velocity of sound in the medium=sqrt((specific heat)(R)(initial temperature)

sqrt((1.4)(287)(243)

sqrt(97637.4)

312.4

given initail mach number is 3

m1=velocity of flow/velocity of sound in medium

3=v/312.4

v=312.4*3

=937.2m/s

across the shock wave the mach number decreases and the corresponding temperature ,pressure and density increases