A converging nozzle is connected to a large tank that contains compressed air at 15°C. The nozzle exit area is 0.001 m 2 . The exhaust is discharged to the atmosphere. To obtain a satisfactory shadow photograph of the flow pattern leaving the nozzle exit, the pressure in the exit plane must be greater than 325 kPa gage. What pressure is required in the tank? What mass flow rate of air must be supplied if the system is to run continuously? Show static and stagnation state points on a Ts diagram.
A converging nozzle is connected to a large tank that contains compressed air at 15°C. The nozzle exit area is 0.001 m 2 . The exhaust is discharged to the atmosphere. To obtain a satisfactory shadow photograph of the flow pattern leaving the nozzle exit, the pressure in the exit plane must be greater than 325 kPa gage. What pressure is required in the tank? What mass flow rate of air must be supplied if the system is to run continuously? Show static and stagnation state points on a Ts diagram.
A converging nozzle is connected to a large tank that contains compressed air at 15°C. The nozzle exit area is 0.001 m2. The exhaust is discharged to the atmosphere. To obtain a satisfactory shadow photograph of the flow pattern leaving the nozzle exit, the pressure in the exit plane must be greater than 325 kPa gage. What pressure is required in the tank? What mass flow rate of air must be supplied if the system is to run continuously? Show static and stagnation state points on a Ts diagram.
NUMBER 1;
Consider a rocket engine burning hydrogen and oxygen; the
combustion chamber (reservoir) pressure and temperature
are 25 atm and 3517 K,
respectively. The
area of the
rocket nozzle throat is 0.1m². The area of the exit is
designed so that the exit pressure is equal to 0.01174
atm. Determine the exit area and exit velocity with the
given parameters:
Mass flow rate = 121.9 kgm/s
Molecular weight (gas mixture)
Specific heat ratio (gas mixture) = 1.22
Universal gas constant = 8,314 J/ (kg/mol) (K)
= 16 mol
3. Assume the turbine as an incompressible flow machine. The average meridional speed is given as 150m/s. The flow coefficient is 0.5. Determine the blade speed that satisfies the above conditions.4. In a two-dimensional compressor cascade, inlet stagnation air pressure is 1.5 bar and inlet stagnation temperature is 330K. For an inlet Mach number of 0.75 and an inlet flow angle of 500, the exit flow angle is measured as 15.80. Determine the mass flow rate per unit frontal area, the exit Mach number and the static pressure ratio across the cascade. Assume the flow is isentropic.
The converging-diverging flow domain is shown in Figure 1. The inlet diameter is 0.2 m, the throat diameter is 0.15 m, and the outlet diameter is 0.24 m. The axial distance from the inlet to the throat is 0.30 m—the same as the axial distance from the throat to the outlet. At the inlet section, the stagnation pressure P0 is set to 220 kPa (absolute), while the stagnation temperature T0, at the inlet is set to 300 K.
Chapter 12 Solutions
Fox And Mcdonald's Introduction To Fluid Mechanics
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