Question

In: Mechanical Engineering

Problem 1: Carbon dioxide flows isentropically at the rate of 1 kg/s through a convergent-divergent nozzle....

Problem 1: Carbon dioxide flows isentropically at the rate of 1 kg/s through a
convergent-divergent nozzle. The stagnation temperature is 310 K and the stagnation
pressure is 1400 kPa. If the exit pressure is 101.3 kPa, determine a) throat area, b) exit
Mach number and c) exit velocity. Assume sonic (M =1) conditions at throat.
(d) plot using MS excel variation of: total temperature, total pressure, total density,
density, temperature, Mach number, velocity, speed of sound along the centre line of

Problem 4: A solid-propellant rocket has the following data: Combustion chamber
temperature = 2600 K, Combustion chamber pressure = 20 MPa. The combustion
gasses flow isentropically through a convergent-divergent nozzle with Throat
diameter = 46 mm, The Exhaust gas constant R = 400 J/(kg · K) with Gas specific
heat ratio γ = 1.2. The Exit pressure = 100 kPa. Calculate: Exit Mach number,
velocity, and mass flow rate.

Solutions

Expert Solution


Related Solutions

Air is supplied to a convergent–divergent nozzle from a large tank in which the pressure and...
Air is supplied to a convergent–divergent nozzle from a large tank in which the pressure and temperature are kept at 700 kPa and 40°C, respectively. If the nozzle has an exit area that is 1.6 times the throat area and if a normal shock occurs in the nozzle at a section where the area is 1.2 times the throat area, find the pressure, temperature, and Mach number at the nozzle exit. Assume one-dimensional, isentropic flow.
A convergent–divergent nozzle with an exit area to throat area ratio of 3 is supplied with...
A convergent–divergent nozzle with an exit area to throat area ratio of 3 is supplied with air from a reservoir in which the pressure is 350 kPa. The air from the nozzle is discharged into another large reservoir. It is found that the flow leaving the nozzle exit is directed inward at an angle of 4° to the nozzle centerline. The velocity on the nozzle exit plane is supersonic. What is the pressure in the second reservoir?
Air is supplied to a convergent–divergent nozzle from a reservoir where the pressure is 100 kPa....
Air is supplied to a convergent–divergent nozzle from a reservoir where the pressure is 100 kPa. The air is then discharged through a short pipe into another reservoir where the pressure can be varied. The cross-sectional area of the pipe is twice the area of the throat of the nozzle. Friction and heat transfer may be neglected throughout the flow. If the discharge pipe has constant cross-sectional area, determine the range of static pressure in the pipe for which a...
Determine whether the integrals are divergent or convergent. Calculate the convergent ones. ?)∫ 1 / ?^2+?...
Determine whether the integrals are divergent or convergent. Calculate the convergent ones. ?)∫ 1 / ?^2+? ?x (from 1 to positive infinity) ?) ∫ ? −√? / √? ?? ( from 1 to positive infinity) ?) ∫ ??????? (negative infinity to positive infinity) ?) ∫ 1 / √3−? ?x ( from 2 to 3)
a mixture of gases consists of 0.1 kg of oxygen, 1 kg of carbon dioxide, and...
a mixture of gases consists of 0.1 kg of oxygen, 1 kg of carbon dioxide, and 0.5 kg of helium is compressed to 17,500 kPa and 20 C. determine volume occupied by the mixture?
3) Air flows steadily at the rate of 0.4 kg/s through an air compressor, entering at...
3) Air flows steadily at the rate of 0.4 kg/s through an air compressor, entering at 6 m/s with a pressure of 1 bar and a specific volume of 0.85 m3/kg, and leaving at 4.5 m/s with       a pressure of 6.9 bar and a specific volume of 0.16 m3/kg. The internal energy of air leaving is 88 kJ/kg greater than that of the air entering. Cooling water in a jacket surrounding the cylinder absorbs heat from the air at...
Calculate the maximum mass flow possible through a frictionless, heat-insulated, convergent nozzle if the entry or...
Calculate the maximum mass flow possible through a frictionless, heat-insulated, convergent nozzle if the entry or stagnation conditions are 5 bar and 15°C and the throat area is 6.5 cm2. Also calculate the temperature of the air at the throat. Take cp = 1.00 kJ kg−1 K−1 and γ = 1.4.
A convergent-divergent duct has a throat area that is 1/3 the area of the inlet. If...
A convergent-divergent duct has a throat area that is 1/3 the area of the inlet. If the pressure at the throat is 95lbft2 less than the pressure at the inlet, what is the inlet velocity, assuming density is .002 slugs/ft3 ?
Hot air flows with a mass flow rate of 0.05 kg/s through an insulated square duct...
Hot air flows with a mass flow rate of 0.05 kg/s through an insulated square duct with side of 0.15m, the hot air enters at 103 oC and after a distance of 5m, cools to 85 oC. The heat transfer coefficient between the duct outer surface and the ambient air (Tair = 0 oC) is 6 W/m2 K. Calculate the heat transfer coefficient between hot air and duct inner wall. Air Cp = 1.011 KJ/kg K; air k = 0.0306...
A stream of carbon dioxide flows at a rate of 15.0 kmol/h. Use the truncated-viralequation-of-state to...
A stream of carbon dioxide flows at a rate of 15.0 kmol/h. Use the truncated-viralequation-of-state to find the volume flow-rate at 60.0 atm and 70.0 oC.
ADVERTISEMENT
ADVERTISEMENT
ADVERTISEMENT