Question

Dry air flows from a reservoir in which the temperature is 200°C and pressure is 600 kPa absolute. a) (20%) Assuming isentropic flow, calculate the temperature, pressure, and velocity when the Mach number is 2.1. T1 = °C P. = kPa 777 Vi = S b) (10%) A normal shock wave forms at the location where the Mach number is 2.1. Calculate the pressure and velocity after the shock wave. P2 = kPa m V2 = S
minimum of 3 significant figures please

Answer 1

The answer for part (a)
Given Day Air Temperature (T.): 200c = 2004 273 = 473K Pressure (p.) = book pa To Find (a) Temp. (a) Temp. (To), Pressure (Po), velocity when Mach no, is 2:1 (Assuming isent ropic flow) solution (a) As we know that, For isentrefoic flow Kis adiabatic index for air k=14 To=Til It [k . To=473 (1+(1.4.1]x (2:13) 2 To = 890.18K Pozpi It [k-1] Ma 는 ( Cousada Po 5486.80 kra To= Ttu? 20p = 82 cp (Tort) = √2 (1.005 ks) + (890118-473) * * 1000 m Egia Ja KI Jv=915.71 m/s

Hence, the stagalin asentropic flow temperature Pressure, 890.18 K, 5486. gokha and 915-71 m/s Velocity are To find aby Mach no. P2 = 4.9783 before shock Pressure and velocity after the shock wave (Ma)=2.1 solution & For Mach no. (Ma) = 2.1 e [P2 is foressure after shock and f, is Pi statico T2 = 1.7705 [I is temp. after shock and T, is before shock] Poz [lo, is pressure after shock wave and Por lo, is before shock wave istagnation condition the pressure after the shock Condition - 0.6742 for Stangel por = Por Pol 0.6742x 5496.80 lez= 3699.2Kla we will find the pressure after the shock. for static condition مس ولم 2 Pi 12 = 4.9783 45486 80 12 = 27 314.93 kPa

Velocity after the shock wave +1_589-19 157.ock - v Since v=2 2 cp (t₂-t) x,... v 2x10.5 (1576.06- 890.18) X.... 1174.14 mis Hence the Temperature and velocity after the shock are 1576.00k, 1174.14 mis respectively And the pressure is 3699.2 kPa ae
is 890.186 K, 5486.809 KPa, and 915.713 m/s

The answer for part (b) is1174.145 m/s and 3699.200 KPa

Please refer images of solution for detailed information

I have find both the pressure in normal and stagnation condition after the normal shock wave in part (b)