Air with a stagnation pressure of 1000 kPa and stagnation temperature of 500 K flows isentropically into a 100 kPA ambient (back) pressure. Calculate the Area ratio at the exit of a nozzle for isentro...
Air with a stagnation pressure of 1000 kPa and stagnation temperature of 500 K flows isentropically into a 100 kPA ambient (back) pressure. Calculate the Area ratio at the exit of a nozzle for isentropic flow with these conditions. Further if flow is considered isentropic within the nozzle calculate the isentropic nozzle efficiency if the area ratio at the nozzle exit were 1.2 rather than your calculated value for isentropic exit conditions above.
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Air with a stagnation pressure of 1000 kPa and stagnation temperature of 500 K flows isentropically into a 100 kPA ambient (back) pressure. Calculate the Area ratio at the exit of a nozzle for isentro...
Air at stagnation pressure of 700 kPa and temperature of 530 K enters a isentropic converging-diverging...
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 enters a nozzle in a jet engine at a pressure of 500 kPa, temperature of...
Air enters a nozzle in a jet engine at a pressure of 500 kPa, temperature of 650K, and velocity of 75 m/s. The air exits the nozzle at a pressure of 100 kPa, and the isentropic nozzle efficiency is 82%. a). Determine the velocity of the air at the nozzle exit. b). Determine the rate of entropy generation in the nozzle per kg of air flowing in kW/kgK
PROBLEM 1 (50 points) Pa= 100 kPa D=0.1 m Po=500 kPa To-300 K Convergent nozzle alone Nozzle Exit Pa 100 kPa f- 0.005 D= 0.1 m Po=500 kPa To-300 K Convergent nozzle + pipe L= 10 m Nozzle Exit Pipe Ex...
PROBLEM 1 (50 points) Pa= 100 kPa D=0.1 m Po=500 kPa To-300 K Convergent nozzle alone Nozzle Exit Pa 100 kPa f- 0.005 D= 0.1 m Po=500 kPa To-300 K Convergent nozzle + pipe L= 10 m Nozzle Exit Pipe Exit A convergent nozzle of diameter D = 0.1 m is connected to a reservoir with pressure po=500 kPa The convergent nozzle supplies flow to a pipe of equal diameter with length L = 10 m and friction factor f...
Normal Shock Nozzle Exit (4, -6 cm? Back pressure Air from a reservoir at 350 K...
Normal Shock Nozzle Exit (4, -6 cm? Back pressure Air from a reservoir at 350 K and 500 kPa, flows through a converging-diverging nozzle. The throat area is 3 cm- and the exit area is 6 cm. A normal shock appears, for which the downstream (region 2) Mach number (M2) is 0.6405. Reservoir Throat (A = 3 cm (a) What is the Mach number (M]) upstream of the shock? 350K, 500 kPa (abs) (b) What is the area where the...
Normal Shock Nozzle Exit (4, -6 cm? Back pressure Air from a reservoir at 350 K...
Normal Shock Nozzle Exit (4, -6 cm? Back pressure Air from a reservoir at 350 K and 500 kPa, flows through a converging-diverging nozzle. The throat area is 3 cm- and the exit area is 6 cm. A normal shock appears, for which the downstream (region 2) Mach number (M2) is 0.6405. Reservoir Throat (A = 3 cm (a) What is the Mach number (M]) upstream of the shock? 350K, 500 kPa (abs) (b) What is the area where the...
Normal Shock Nozzle Exit (4, -6 cm? Back pressure Air from a reservoir at 350 K...
Normal Shock Nozzle Exit (4, -6 cm? Back pressure Air from a reservoir at 350 K and 500 kPa, flows through a converging-diverging nozzle. The throat area is 3 cm- and the exit area is 6 cm. A normal shock appears, for which the downstream (region 2) Mach number (M2) is 0.6405. Reservoir Throat (A = 3 cm (a) What is the Mach number (M]) upstream of the shock? 350K, 500 kPa (abs) (b) What is the area where the...
A converging-diverging nozzle is designed for M - 2.5 at the exit. Air is supplied at 1000 kPa and 400 K. At design, what is the exit pressure, temperature and speed? b'At design, wh...
A converging-diverging nozzle is designed for M - 2.5 at the exit. Air is supplied at 1000 kPa and 400 K. At design, what is the exit pressure, temperature and speed? b'At design, what is the throat pressure and temperature? c. What are the Mach number and speed (m/s) at the throat? I d. If the flow in the nozzle is isentropic, but a normal shock forms at the exit plane, what are the pressure, temperature and Mach number downstream...
P, Combustion Chamber P2 Nozzle Exit P3 Ambient atmosphere Note: for perfect expansion, if y is k...
We were unable to transcribe this imageWe were unable to transcribe this imageP, Combustion Chamber P2 Nozzle Exit P3 Ambient atmosphere Note: for perfect expansion, if y is known, pressure ratio and e are not independent. Could 22use isentropic compressible flow solver 1How to improve thrust? 20 Decrease γ Increase p,/P3 20 1.40 60 10 em 5 1.3 1.2 10 20 50 100 200 500 1000 2000 5000 10,000 FIGURE 3-6 Thrust coefficient Cp as a function of pressure ratio,...
[15 pts] Consider a converging diverging nozzle with an exit-to-throat area ratio of Ae/At = 1.25...
[15 pts] Consider a converging diverging nozzle with an exit-to-throat area ratio of Ae/At = 1.25 as shown below. The stagnation pressure upstream of the throat is 8.5 atm and the stagnation temperature is 1000 K. (a) Assume the air is expanded isentropically to supersonic speed at the exit. Determine the following properties at the nozzle exit: Me, Pe, Te, Pe, ue, Poe, Toe (b) If the area ratio in the subsonic part of the converging diverging nozzle, A1/A is...
The throat area of a rocket nozzle is 5 cm2. The exit to throat area ratio...
The throat area of a rocket nozzle is 5 cm2. The exit to throat area ratio is 2.9. The chamber pressure is 20 atm and the chamber temperature is 2800 k. what is the maximum possible mass flow rate through the nozzle. assume one dimensional isentropic flow inside the nozzle . If the ambient pressure at the exit is p =0.1 atm , is the flow over expanded or underexpanded?
PROBLEM 1 (50 points) Pa= 100 kPa D=0.1 m Po=500 kPa To-300 K Convergent nozzle alone Nozzle Exit Pa 100 kPa f- 0.005 D= 0.1 m Po=500 kPa To-300 K Convergent nozzle + pipe L= 10 m Nozzle Exit Pipe Exit A convergent nozzle of diameter D = 0.1 m is connected to a reservoir with pressure po=500 kPa The convergent nozzle supplies flow to a pipe of equal diameter with length L = 10 m and friction factor f...
Normal Shock Nozzle Exit (4, -6 cm? Back pressure Air from a reservoir at 350 K and 500 kPa, flows through a converging-diverging nozzle. The throat area is 3 cm- and the exit area is 6 cm. A normal shock appears, for which the downstream (region 2) Mach number (M2) is 0.6405. Reservoir Throat (A = 3 cm (a) What is the Mach number (M]) upstream of the shock? 350K, 500 kPa (abs) (b) What is the area where the...
Normal Shock Nozzle Exit (4, -6 cm? Back pressure Air from a reservoir at 350 K and 500 kPa, flows through a converging-diverging nozzle. The throat area is 3 cm- and the exit area is 6 cm. A normal shock appears, for which the downstream (region 2) Mach number (M2) is 0.6405. Reservoir Throat (A = 3 cm (a) What is the Mach number (M]) upstream of the shock? 350K, 500 kPa (abs) (b) What is the area where the...
Normal Shock Nozzle Exit (4, -6 cm? Back pressure Air from a reservoir at 350 K and 500 kPa, flows through a converging-diverging nozzle. The throat area is 3 cm- and the exit area is 6 cm. A normal shock appears, for which the downstream (region 2) Mach number (M2) is 0.6405. Reservoir Throat (A = 3 cm (a) What is the Mach number (M]) upstream of the shock? 350K, 500 kPa (abs) (b) What is the area where the...
A converging-diverging nozzle is designed for M - 2.5 at the exit. Air is supplied at 1000 kPa and 400 K. At design, what is the exit pressure, temperature and speed? b'At design, what is the throat pressure and temperature? c. What are the Mach number and speed (m/s) at the throat? I d. If the flow in the nozzle is isentropic, but a normal shock forms at the exit plane, what are the pressure, temperature and Mach number downstream...
We were unable to transcribe this imageWe were unable to transcribe this imageP, Combustion Chamber P2 Nozzle Exit P3 Ambient atmosphere Note: for perfect expansion, if y is known, pressure ratio and e are not independent. Could 22use isentropic compressible flow solver 1How to improve thrust? 20 Decrease γ Increase p,/P3 20 1.40 60 10 em 5 1.3 1.2 10 20 50 100 200 500 1000 2000 5000 10,000 FIGURE 3-6 Thrust coefficient Cp as a function of pressure ratio,...
[15 pts] Consider a converging diverging nozzle with an exit-to-throat area ratio of Ae/At = 1.25 as shown below. The stagnation pressure upstream of the throat is 8.5 atm and the stagnation temperature is 1000 K. (a) Assume the air is expanded isentropically to supersonic speed at the exit. Determine the following properties at the nozzle exit: Me, Pe, Te, Pe, ue, Poe, Toe (b) If the area ratio in the subsonic part of the converging diverging nozzle, A1/A is...
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