COMPRESSIBLE FLOW 903
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\M-therm\Th16-2.pm5- Air is released from one tank to another through a convergent-divergent nozzle at the rate of 12 N/s. The
supply tank is at a pressure of 400 kN/m^2 and temperature 110°C, and the pressure in the receiving tank
is 100 kN/m^2. Determine : (i) The pressure, temperature, and Mach number in the constriction, (ii) The
required diameter of constriction, (iii) The diameter of the nozzle at the exit for full expansion, and the
Mach number. [Ans. (i) 210 kN/m^2 ; 319 K, (ii) 43.5 mm ; (iii) 48 mm ; 1.56] - Oxygen flows in a conduit at an absolute pressure of 170 kN/m^2. If the absolute pressure and temperature
at the nose of small object in the stream are 200 kN/m^2 and 70.16°C respectively, determine the velocity in
the conduit. Take γ = 1.4 and R = 281.43 J/kg K. [Ans. 175.3 m/s] - Air at a velocity of 1400 km/h has a pressure of 10 kN/m^2 vacuum and temperature of 50.16°C. Calculate
local Mach number and stagnation pressure, density and temperature. Take γ = 1.4, R = 281.43 J/kg K and
barometric pressure = 101.325 kN/m^2 .[Ans. 1.089 ; 192.358 kN/m^2 ; 1.708 kg/m^3 ; 399.8 K] - A normal shock wave occurs in a diverging section when air is flowing at a velocity of 420 m/s, pressure
100 kN/m^2 , and temperature 10°C. Determine : (i) The Mach number before and after the shock, (ii) The
pressure rise, and (iii) The velocity and temperature after the shock.
[Ans. (i) 1.25 ; 0.91 ; (ii) 66 kN/m^2 , (iii) 292 m/s ; 54°C] - A normal shock wave occurs in air flowing at a Mach number of 1.5. The static pressure and temperature
of the air upstream of the shock wave are 100 kN/m^2 and 300 K. Determine the Mach number, pressure
and temperature downstream of the shockwave. Also estimate the shock strength.
[Ans. 0.7 ; 246 kN/m^2 ; 396.17 K ; 1.46]