This problem illustrates the effects of normal shock wave on an isentropic flow through a converging-diverging...
UBAV Air flows through a converging-diverging nozzle diffuser. A normal shock stands in the diverging section of the nozzle. Assuming isentropie flow, air as an ideal gas, and constant specific heat determine the state at several locations in the system. Solve wsing equations rather than with the tables Note: The Specific heat ratio and gas constant for air are given as k-1 and R 0.287 kJ/kg-K respectively Give Values Inlet Temperature: TI(K)-340 Inlet pressure: P1 (kPa) - 550 Inlet Velocity:...
Poblem Comergini sentropie regim (no shock waves) Consider isentropic flow through a converging-diverging nozzle. The exit area of the nozzle is , and the throat area of the nozzle is . The air entering the nozzle has stagnation conditions: , and Use Figure D.1 or Table D (a) Calculate the mass flow rate for choked flow (that is, sonic flow at the throat). Hints: See Section 11.7, use Figure D.1 to find density and temperature at M 1 (throat), find...
Air at stagnation pressure of 700 kPa and temperature of 530 K enters a isentropic converging-diverging nozzle. The throat area of the nozzle is 5 cm2, the exit area is 12.5 cm2. The back pressure is 350 kPa and a normal shock occurs within a diverging section. Determine (a) exit Mach number, (b) change in stagnation pressure, (c) upstream and downstream Mach number of shock (d) cross sectional area where shock occurs (e) back pressure if the flow were isentropic...
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) = 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...
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) = 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...
A converging-diverging nozzle has a throat area of 1 cm2 and an exit area of 4 cm2. The inlet stagnation conditions are Po 500 kPa and To 300 K. The nozzle discharges to an infinite surroundings at Po. The flowing medium is air as a perfect gas with k-1.4 Answer the following: i What are the two isentropic flow solutions for this nozzle with M 1 at the throat? What are the Mach number, P, Po and T, To at...
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) =...