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Y-3 Xo Air ((p = 1.05 kJ/kg k) ra138) at Nim²...
Q6 (a) Explain briefly the different between incompressible and compressible fluid flow (5 marks) (6) Air...
Q6 (a) Explain briefly the different between incompressible and compressible fluid flow (5 marks) (6) Air at pressure and temperature of 200 kPa, 373.2 K flows through a duct at Mach Number of 0.8. The gas constant and specific heat ratio of air are 0.287 kJ/kg k, 1.4 respectively. Determine, (1) air velocity: (11) stagnation pressure: (111) stagnation temperature and (iv) stagnation density (8 marks) Nitrogen enters a converging diverging nozzle from a reservoir at a pressure of 700 kPa...
For air, y- 1.4, cp 1.005 k]/kg K, R- 0.287 kJ/kg K unless stated in question....
For air, y- 1.4, cp 1.005 k]/kg K, R- 0.287 kJ/kg K unless stated in question. 1. Air flows adiabatically through a duct. At point 1 the velocity is 240m/s, with T1 - 320 K and p1 170 kPa. Compute i. To ii. (Mach number) ii. At point 2 further downstream V2-290 m/s and P2-135 kPa. What is the stagnation pressure Po2 Hints: Given the properties it is easy to solve for the Mach number using the following formulas To/T...
Fundamentals-of-Compressible-Fluid-Dynamics Balachandra Chapter 3 7. Air at 3 bar and 300 K enter...
Fundamentals-of-Compressible-Fluid-Dynamics Balachandra Chapter 3 7. Air at 3 bar and 300 K enters a duct of varying cross-sectional area of 150m/s. at inlet scetion the area is 0.05 m2. At another section downstream of it, the fluid properties are 2 bar and 280K with a flow velocity of 250m/s, Assuming air to be perfect gas, find the internal thrust produced. H [Ans. -1586.74 N] 8. The entry conditions of air into horizontal duct are 300K 345kPa and 150 m/s the...
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...
u. 107 y. 10° Q.10 (kg/m) 0.9950 (kJ/kg.K) 1.009 (N.s/m?) 208.2 (mʻ/s) 20.92 k. 10 (W/m.K)...
u. 107 y. 10° Q.10 (kg/m) 0.9950 (kJ/kg.K) 1.009 (N.s/m?) 208.2 (mʻ/s) 20.92 k. 10 (W/m.K) 30.0 (m²/s) 29.9 Pr 0.700 Air at p = latm enters a thin-walled long tube at an inlet temperature of Tmi = 100 °C. The diameter and length of the tube are 5 mm and 2 m respectively. A constant heat flux is applied to the air from the tube surface. The air mass flow rate is ṁ = 135 x 10-kg/s. (a) Is...
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 the system. Solve using equations rather than with the tables. 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) = 353 Inlet pressure: Pl (kPa) = 546 Inlet Velocity: V1 (m/s) = 61 Area at nozzle inlet: A1 (cm^2) = 7.24...
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) = 338 Inlet pressure: P1 (kPa) = 555 Inlet Velocity: V1 (m/s) = 121 Area at inlet (cm^2) = 9 Mach number at the exit = 1.56 a) Determine...
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. Solve using equations rather than with the tables. 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) = 321 Inlet pressure: P1 (kPa) = 588 Inlet Velocity: V1 (m/s) = 97 Area at nozzle inlet: A1 (cm^2) =...
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. Solve using equations rather than with the tables. 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) 370 Inlet pressure: P1 (kPa) = 576 Inlet Velocity: V1 (m/s) - 106 Area at nozzle inlet: A1 (cm^2) = 8.32...
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. Solve using equations rather than with the tables. 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) = 348 Inlet pressure: P1 (kPa) = 544 Inlet Velocity: V1 (m/s) = 122 Area at nozzle inlet: A1 (cm^2) =...
Q6 (a) Explain briefly the different between incompressible and compressible fluid flow (5 marks) (6) Air at pressure and temperature of 200 kPa, 373.2 K flows through a duct at Mach Number of 0.8. The gas constant and specific heat ratio of air are 0.287 kJ/kg k, 1.4 respectively. Determine, (1) air velocity: (11) stagnation pressure: (111) stagnation temperature and (iv) stagnation density (8 marks) Nitrogen enters a converging diverging nozzle from a reservoir at a pressure of 700 kPa...
For air, y- 1.4, cp 1.005 k]/kg K, R- 0.287 kJ/kg K unless stated in question. 1. Air flows adiabatically through a duct. At point 1 the velocity is 240m/s, with T1 - 320 K and p1 170 kPa. Compute i. To ii. (Mach number) ii. At point 2 further downstream V2-290 m/s and P2-135 kPa. What is the stagnation pressure Po2 Hints: Given the properties it is easy to solve for the Mach number using the following formulas To/T...
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...
u. 107 y. 10° Q.10 (kg/m) 0.9950 (kJ/kg.K) 1.009 (N.s/m?) 208.2 (mʻ/s) 20.92 k. 10 (W/m.K) 30.0 (m²/s) 29.9 Pr 0.700 Air at p = latm enters a thin-walled long tube at an inlet temperature of Tmi = 100 °C. The diameter and length of the tube are 5 mm and 2 m respectively. A constant heat flux is applied to the air from the tube surface. The air mass flow rate is ṁ = 135 x 10-kg/s. (a) Is...
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 the system. Solve using equations rather than with the tables. 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) = 353 Inlet pressure: Pl (kPa) = 546 Inlet Velocity: V1 (m/s) = 61 Area at nozzle inlet: A1 (cm^2) = 7.24...
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) = 338 Inlet pressure: P1 (kPa) = 555 Inlet Velocity: V1 (m/s) = 121 Area at inlet (cm^2) = 9 Mach number at the exit = 1.56 a) Determine...
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. Solve using equations rather than with the tables. 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) 370 Inlet pressure: P1 (kPa) = 576 Inlet Velocity: V1 (m/s) - 106 Area at nozzle inlet: A1 (cm^2) = 8.32...
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. Solve using equations rather than with the tables. 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) = 348 Inlet pressure: P1 (kPa) = 544 Inlet Velocity: V1 (m/s) = 122 Area at nozzle inlet: A1 (cm^2) =...
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