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4. CO2 flows steadily through the duct shown from 350 kPa, 60°C, and 120 m/s at...
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...
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...
asap please, will rate! 3. Water flows steadily through a curved duct that turns the flow...
asap please, will rate!
3. Water flows steadily through a curved duct that turns the flow through angle 0= 135º, as shown in Fig. 3. The cross-sectional area of the duct changes from Aj 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 Bi= 1.01 at the duct inlet and B2 = 1.03 at the...
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...
4.) Air flows adiabatically through a duct. At point (1) the velocity is 200 m/s with...
4.) Air flows adiabatically through a duct. At point (1) the velocity is 200 m/s with a temperature of 310 K and pressure of 180 kPa. Compute a.) T., b.) Pol, c.) po, d.) Ma, e.) Vmax, f.) V*. At point (2) further downstream the velocity is 270 m/s and pressure is 125 kPa, g.) what is the stagnation pressure P.2?
Air is compressed steadily by a reversible compressor from an inlet state of 100 kPa and...
Air is compressed steadily by a reversible compressor from an inlet state of 100 kPa and 300 K to an exit pressure of 900 kPa. if the volume flow rate = 1 m/sec Determine: the compressor power (kW) for isentropic compression with k = 1.4 Choose... the compressor power (kW) for polytropic compression with n = 1.3 Choose.. the compressor power (kW) for ideal two stage compression with intercooling with a polytropic exponent of 1.3 Choose... the compressor power (kW)...
Steam with the mass flow rate of 0.75 kg/s enters an adiabatic turbine steadily at 19 MPa, 600°C and 150 m/s
Steam with the mass flow rate of 0.75 kg/s enters an adiabatic turbine steadily at 19 MPa, 600°C and 150 m/s, and leaves at 150 kPa and 350 m/s. The isentropic efficiency of the turbine is 85%. Neglect potential energy. (I) Determine the exit temperature of the steam, and its quality (if saturated mixture) (ii) Calculate the actual power output of the turbine, in kW (iii) Illustrate a T-s diagram with respect to saturation lines for the isentropic process by clearly indicating all pressure, temperature,...
Air at 10°C and 80 kPa (static values) enters the diffuser of a jet engine steadily...
Air at 10°C and 80 kPa (static values) enters the diffuser of a jet engine steadily with a velocity of 200 m/s. The inlet area of the diffuser is 0.4 m2. The air leaves the diffuser with a velocity of 40 m/s. Calculate 1) air density 2) air mass flow 3) inlet stagnation temprature 4) Inlet stgnation enthelpy 5) Outlet static temprature T2 a. 0.98 kg/m3 b. 1.01 kq/m3 c. 1.33 kg/m3 d. 90.1 kg/s e. 88.3 kg/m3 78.8 kg/m3...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant specific heats determine the state at several locations in the system. Note: The specific heat ratio and gas constant for air are given as k=1.4 and R=0.287 kJ/kg-K respectively. --Given Values-- Inlet Temperature: T1 (K) = 360 Inlet pressure: P1 (kPa) = 583 Inlet Velocity: V1 (m/s) = 105 Area at inlet (cm^2) = 8.2 Mach number at the exit = 1.86 a) Determine...
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...
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...
asap please, will rate!
3. Water flows steadily through a curved duct that turns the flow through angle 0= 135º, as shown in Fig. 3. The cross-sectional area of the duct changes from Aj 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 Bi= 1.01 at the duct inlet and B2 = 1.03 at the...
4.) Air flows adiabatically through a duct. At point (1) the velocity is 200 m/s with a temperature of 310 K and pressure of 180 kPa. Compute a.) T., b.) Pol, c.) po, d.) Ma, e.) Vmax, f.) V*. At point (2) further downstream the velocity is 270 m/s and pressure is 125 kPa, g.) what is the stagnation pressure P.2?
Air is compressed steadily by a reversible compressor from an inlet state of 100 kPa and 300 K to an exit pressure of 900 kPa. if the volume flow rate = 1 m/sec Determine: the compressor power (kW) for isentropic compression with k = 1.4 Choose... the compressor power (kW) for polytropic compression with n = 1.3 Choose.. the compressor power (kW) for ideal two stage compression with intercooling with a polytropic exponent of 1.3 Choose... the compressor power (kW)...
Air at 10°C and 80 kPa (static values) enters the diffuser of a jet engine steadily with a velocity of 200 m/s. The inlet area of the diffuser is 0.4 m2. The air leaves the diffuser with a velocity of 40 m/s. Calculate 1) air density 2) air mass flow 3) inlet stagnation temprature 4) Inlet stgnation enthelpy 5) Outlet static temprature T2 a. 0.98 kg/m3 b. 1.01 kq/m3 c. 1.33 kg/m3 d. 90.1 kg/s e. 88.3 kg/m3 78.8 kg/m3...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant specific heats determine the state at several locations in the system. Note: The specific heat ratio and gas constant for air are given as k=1.4 and R=0.287 kJ/kg-K respectively. --Given Values-- Inlet Temperature: T1 (K) = 360 Inlet pressure: P1 (kPa) = 583 Inlet Velocity: V1 (m/s) = 105 Area at inlet (cm^2) = 8.2 Mach number at the exit = 1.86 a) Determine...
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