Carbon dioxide flows steadily through a varying cross-sectional area duct such as a nozzle at a...
Carbon dioxide flows steadily through a varying cross-sectional area duct such as a nozzle at a mass flow rate of 3.00 kg/s. The carbon dioxide enters the duct at a pressure of 1400 kPa and 200?C with a low velocity and expands in the nozzle to a pressure of 1200 kPa. The duct is designed so that the flow can be approximated as isentropic. Determine the density, velocity, flow area, and Mach number at each location along the duct that corresponds to a pressure drop of 1200 kPa. For simplicity, use Cp= 0.846 kJ/kg.K and k=1.289 throughout calculation. Also R for carbon dioxide is 0.1889 kJ/kg.K.
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Carbon dioxide flows steadily through a varying cross-sectional
area duct such as a nozzle at a...
Problem No. 4 (20 Points) Carbon dioxide flows through a converging nozzle with exit diameter of...
Problem No. 4 (20 Points) Carbon dioxide flows through a converging nozzle with exit diameter of 2.5 cm from a reservoir at stagnation pressure of 500 kPa and exits to back pressure of 100 kPa at temperature of 300 K. a) Find the exit plane Mach number and exit plane velocity. b) Calculate the mass flow rate through this nozzle?
Carbon dioxide enters an adiabatic nozzle steadily at 1 MPa and 500°C with a mass flow...
Carbon dioxide enters an adiabatic nozzle steadily at 1 MPa and 500°C with a mass flow rate of 6000 kg/h and leaves at 100 kPa and 450 m/s. The inlet area of the nozzle is 40 cm2 Determine (a) the inlet velocity and (b) the exit temperature.
QUESTION 2 Carbon dioxide enters an adiabatic nozzle steadily at 1 MP, 481 °C, and mass...
QUESTION 2 Carbon dioxide enters an adiabatic nozzle steadily at 1 MP, 481 °C, and mass flow rate of 6,706 kg/h and exits the system at 110 kPa and 468 m/s. Considering the nozzle having an inlet area of 45 cm, calculate the inlet velocity in m/s (Give your answer with three decimals, and do NOT enter units!!!).
ANSWER [0.54 and 1.63] (b) Air flows through a converging-diverging nozzle. At point "A" in the converging section, the cross-sectional area is 50 cm2 and the Mach number was measured to b...
ANSWER [0.54 and 1.63]
(b) Air flows through a converging-diverging nozzle. At point "A" in the converging section, the cross-sectional area is 50 cm2 and the Mach number was measured to be 0.4. At point "B" in the diverging section, the cross-sectional area is 40 cm2. Find the possible Mach numbers at point "B" Assume that the flow is isentropic and the air specific ratio γ-1.4 and the gas constant R: 287 J/kg K.
(b) Air flows through a converging-diverging...
Determine the area and velocity at the exit of the convergent nozzle through which it flows...
Determine the area and velocity at the exit of the convergent nozzle through which it flows an isentropic gas (k = 1,4; R = 287Nm/kg.K). What is the lowest possible value for the outlet of the nozzle while maintaining isoentropic flow? (For the same input conditions). Data: Pressure1 = 207 kPa ; Density1 = 1,3 kg/m³ ; Velocity1 = 47,2 m/s ; Area1 = 0,1m² . Pressure2 = 172,5 kPa
Water flows steadily through a curved duct that turns the flow through angle = 135 degrees,...
Water flows steadily through a curved duct that turns the flow
through angle = 135 degrees, as shown in Fig. 3. The
cross-sectional area of the duct changes from A1 = 0.025 m2 at the
inlet to A2 = 0.05 m2 at the outlet. The average velocity at the
duct inlet is V1 = 6 m/s. The momentum flux correction factor may
be taken as 1 = 1.01 at the duct inlet and 2 = 1.03 at the its
outlet....
Water flows steadily through a curved duct that turns the flow through angle @= 135º, as...
Water flows steadily through a curved duct that turns the flow through angle @= 135º, as shown in Fig. 3. The cross-sectional area of the duct changes from A1 = 0.025 m² at the inlet to A2 = 0.05 m’ at the outlet. The average velocity at the duct inlet is V1 = 6 m/s. The momentum flux correction factor may be taken as B1 = 1.01 at the duct inlet and B2 = 1.03 at the its outlet. The...
4. CO2 flows steadily through the duct shown from 350 kPa, 60°C, and 120 m/s at...
4. CO2 flows steadily through the duct shown from 350 kPa, 60°C, and 120 m/s at the inlet state to M -1.3 at the outlet, where local isentropic stagnation conditions are known to be 385 kPa and 350 K. Compute the local isentropic stagnation pressure and temperature at the inlet and the static pressure and temperature at the duct outlet. Flow Inlet Outlet
9. A constant-area duct connected to a C-D nozzle with 1,687. The nozzle is fed by...
9. A constant-area duct connected to a C-D nozzle with 1,687. The nozzle is fed by a large compress-air tank with pressure of 700 kPa and temperature of 540 K. The flow is shockless everywhere and is supersonic at the nozzle exit. Between section 1 and 2, heat added into the duct at a rate of 100.4 kJ/(kg of air). Assuming frictionless flow and ideal gas. Find these properties at section 2: M2. P2.T2 and Poz. 1, nozzle exit Po...
please help...add sketch Water flows steadily through a curved duct that turns the flow through angle...
please help...add sketch
Water flows steadily through a curved duct that turns the flow through angle = 1359, as shown in Fig. 3. The cross-sectional area of the duct changes from A1 = 0.025 m’ at the inlet to Az = 0.05 m² at the outlet. The average velocity at the duct inlet is V1 = 6 m/s. The momentum flux correction factor may be taken as B - 1.01 at the duct inlet and B = 1.03 at the...
Problem No. 4 (20 Points) Carbon dioxide flows through a converging nozzle with exit diameter of 2.5 cm from a reservoir at stagnation pressure of 500 kPa and exits to back pressure of 100 kPa at temperature of 300 K. a) Find the exit plane Mach number and exit plane velocity. b) Calculate the mass flow rate through this nozzle?
QUESTION 2 Carbon dioxide enters an adiabatic nozzle steadily at 1 MP, 481 °C, and mass flow rate of 6,706 kg/h and exits the system at 110 kPa and 468 m/s. Considering the nozzle having an inlet area of 45 cm, calculate the inlet velocity in m/s (Give your answer with three decimals, and do NOT enter units!!!).
ANSWER [0.54 and 1.63]
(b) Air flows through a converging-diverging nozzle. At point "A" in the converging section, the cross-sectional area is 50 cm2 and the Mach number was measured to be 0.4. At point "B" in the diverging section, the cross-sectional area is 40 cm2. Find the possible Mach numbers at point "B" Assume that the flow is isentropic and the air specific ratio γ-1.4 and the gas constant R: 287 J/kg K.
(b) Air flows through a converging-diverging...
Water flows steadily through a curved duct that turns the flow
through angle = 135 degrees, as shown in Fig. 3. The
cross-sectional area of the duct changes from A1 = 0.025 m2 at the
inlet to A2 = 0.05 m2 at the outlet. The average velocity at the
duct inlet is V1 = 6 m/s. The momentum flux correction factor may
be taken as 1 = 1.01 at the duct inlet and 2 = 1.03 at the its
outlet....
Water flows steadily through a curved duct that turns the flow through angle @= 135º, as shown in Fig. 3. The cross-sectional area of the duct changes from A1 = 0.025 m² at the inlet to A2 = 0.05 m’ at the outlet. The average velocity at the duct inlet is V1 = 6 m/s. The momentum flux correction factor may be taken as B1 = 1.01 at the duct inlet and B2 = 1.03 at the its outlet. The...
4. CO2 flows steadily through the duct shown from 350 kPa, 60°C, and 120 m/s at the inlet state to M -1.3 at the outlet, where local isentropic stagnation conditions are known to be 385 kPa and 350 K. Compute the local isentropic stagnation pressure and temperature at the inlet and the static pressure and temperature at the duct outlet. Flow Inlet Outlet
9. A constant-area duct connected to a C-D nozzle with 1,687. The nozzle is fed by a large compress-air tank with pressure of 700 kPa and temperature of 540 K. The flow is shockless everywhere and is supersonic at the nozzle exit. Between section 1 and 2, heat added into the duct at a rate of 100.4 kJ/(kg of air). Assuming frictionless flow and ideal gas. Find these properties at section 2: M2. P2.T2 and Poz. 1, nozzle exit Po...
please help...add sketch
Water flows steadily through a curved duct that turns the flow through angle = 1359, as shown in Fig. 3. The cross-sectional area of the duct changes from A1 = 0.025 m’ at the inlet to Az = 0.05 m² at the outlet. The average velocity at the duct inlet is V1 = 6 m/s. The momentum flux correction factor may be taken as B - 1.01 at the duct inlet and B = 1.03 at the...
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