Air at P1=3 bar, T1=288k, M1=1.5 is brought to sonic velocity in a frictionless constant area duct thought which heat transfer can occur:
1. Determine the final pressure and temperature and the heat add during the process
2. What will be the Mach number, pressure and temperature of air if this heat is extracted from the air?
Air at P1=3 bar, T1=288k, M1=1.5 is brought to sonic velocity in a frictionless constant area...
Air flows through a constant area duct. The pressure and temperature of the air at the inlet to the duct are P1 = 100 kPa absolute, and T1 = 298 K, respectively. Inlet Mach number is M1 = 0.1. Heat is transferred to the air as it flows through the duct and as a result the Mach number at the exit increases. a) Find the pressure and temperature at the exit, while the exit Mach number changes between M=0.2 to...
Conditions before a shock are T1 = 40°C, p1 = 1.2 bar, and M1 = 3.0. An oblique shock is observed at 45° to the approaching air flow. (a) Determine the Mach number and flow direction after the shock. (b) What are the temperature and pressure after the shock?’ (c) Is this a weak or a strong shock?
The C-D nozzle is isentropic; the shock @ entrance to constant area frictionless duct. M1 = 2.0, P1 = 10 psia, T1 = 500 R a) If the back pressure is 31 psia, determine the heat transfer (Btu/lbm) b) Determine stagnation pressure loss Please solve all parts of the problem clearly... Thanks ys! W Ishock e lentrance Pilvo psia Solo ORDI esper seiki vs tra và • W.28279.00. Vale . Avec Bengue 2 In the black pressures LB1 bsial determine...
3. Air enters a constant area duct at a Mach number of 0.14, a pressure of 195 kPa, and a temperature of 25 °C. Heat is added to the air that flows through the duct at a rate of 65 kJ/kg of air. Assuming that the flow is steady and that the effects of wall friction can be ignored, find the temperature, pressure, and Mach number at which the air leaves the duct. Assume that the air behaves as a...
V-3. Air flows at steady state through a horizontal, well-insulated, constant-area duct whose diameter is 0.75 in. At the inlet, p1 = 55.9 lbf/in.2, T1 = 7200R, and the velocity is 9 ft/s. The temperature of the air leaving the duct is 700°R. Determine (a) the velocity at the exit, in ft/s. (b) the pressure at the exit, in lbf/in.2 (c) the magnitude of the net horizontal force exerted by the duct wall on the air, in lbf. In which...
Question 4 (16 Marks) A frictionless, adiabatic compressor compresses hydrogen at a pressure of 3 bar and a temperature of 10 °C, to a pressure of 16 bar. The hydrogen enters the compressor at a velocity of 80 m/s and exits at negligible velocity. From the compressor, the hydrogen is passed at constant pressure through a duct and cooled to a temperature of 55 °C, in the process. The hydrogen mass flow rate is 0.5 kg/s, and all changes in...
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 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) =...
At the beginning of the compression process of an air-standard Otto cycle, P1 = 1.0 bar, T1 = 290 K, V1 = 400 cm3. The maximum temperature in the cycle is 2200 K and the compression ratio is 8. Determine: a) the heat addition in kJ, b) the net work in kJ, c) the thermal efficiency, and d) the mean effective pressure, in bar.