Homework Answers
Flow through the nozzle gets choked as the result of continues reductions in the back pressure to such an extent that
further reduction can't move the point away from the throat.
* As the exit pressure decreases on a choked nozzle , mass flow rate also gets decreased.
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Under what conditions will the flow through a cvergent-divergent nozzle become choked? What happens to the...
Question 1.4 A convergent-divergent nozzle is designed to operate with isentropic flow with an exit Mach number, Me. The flowin the nozzle is supplied from a reservoir of air with a static pressure o...
Question 1.4 A convergent-divergent nozzle is designed to operate with isentropic flow with an exit Mach number, Me. The flowin the nozzle is supplied from a reservoir of air with a static pressure ofPr and a static temperature of Tr and the nozzle has a throat area, AT, as specified in the table below Value Unit Design Data Exit Mach number (ME) 0.55 Area of throat (AT) 600 kPa Reservoir static pressure (PR) 380 WAT Reservoir static temperature (TR) kPa...
Consider a converging-diverging nozzle with subsonic inlet conditions. Answer with justification. Use the sketch of the...
Consider a converging-diverging nozzle with subsonic inlet conditions. Answer with justification. Use the sketch of the pressure diagram wherever appropriate. Gamma = 1.4. R = 286.9 J/kg-K It is given that when the exit pressure is 1MPa, a certain nozzle is operating under choked, subsonic and isentropic conditions. The mass flow rate is found to be 1000 kg/s. What will be the mass flow rate if the exit pressure is 100 kPa? Explain.
Can you please help me with part (e), thanks! A B 72 Question 1.4 A convergent-divergent nozzle is designed to operate...
Can you please help me with part (e), thanks!
A B 72 Question 1.4 A convergent-divergent nozzle is designed to operate with isentropic flow with an exit Mach number, Me. The flow in the nozzle is supplied from a reservoir of air with a static pressure of PR and a static temperature of TR and the nozzle has a throat area, AT, as specified in the table below 73 Design Data Value Unit 75 Exit Mach number (ME) 76 77...
Poblem Comergini sentropie regim (no shock waves) Consider isentropic flow through a converging-diverging nozzle. The exit...
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...
5-1) (15) Estimate the exit pressure of the convergent-divergent nozzle for stable supersonic flow in the...
5-1) (15) Estimate the exit pressure of the convergent-divergent nozzle for stable supersonic flow in the high-pressure turbine with the ratio of the exit area to the throat area of 1.1 with the throat diameter of 1cm and Get the exit steam velocity: (y = 1.4)
A converging-diverging nozzle has a throat area of 1 cm2 and an exit area of 4 cm2. The inlet sta...
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...
Problem 2 was... Air exapands in a frictionless adiabatic flow through a converging-diverging nozzle at a...
Problem 2 was...
Air exapands in a frictionless adiabatic flow through a
converging-diverging nozzle at a mass flow rate of 2.5 kg/s. Source
stagnation condition are 1.1 Mpa and 115 C. If the nozzle exit
pressure is 141 kPa, and there are no shocks in the nozzle, find
the (a) the exit area Ae; (b) the throat At.
And I got (a) Ae = 1.11 * 10^(-3) m^2 and (b) At = 1.87 *
10^(-3) m^2
3. For the nozzle...
A nozzle is designed to deliver a supersonic air flow, R = 287 J/Kg/K, of Mach...
A nozzle is designed to deliver a supersonic air flow, R = 287 J/Kg/K, of Mach M = 2.19 The reservoir has a pressure of p0 = 648kPa and T0= 300K. The nozzle exit has an area of 0.233 m^2. The nozzle flow exits into an environment that is kept at constant pressure pb which matches the exit pressure of the nozzle. As long as there are no shock waves appearing in – or outside the nozzle, the complete flow...
Air enters an isothermal nozzle at a temperature of 300 K, and a velocity of 10...
Air enters an isothermal nozzle at a temperature of 300 K, and a velocity of 10 m/s. The nozzle is very poorly insulated, causing a stray heat transfer rate of 10 kW into the system. The outlet of the nozzle is exposed to an ambient pressure of 1 bar and is choked (Mach = 1). If the area ratio of the nozzle (A, /A2) is 5, what is: The velocity of the nozzle outlet, in [m/s], if the specific heat...
2. Air enters an isothermal nozzle at a temperature of 300 K, and a velocity of...
2. Air enters an isothermal nozzle at a temperature of 300 K, and a velocity of 10 m/s. The nozzle is very poorly insulated, causing a stray heat transfer rate of 10 kW into the system. The outlet of the nozzle is exposed to an ambient pressure of 1 bar and is choked (Mach 1. If the area ratio of the nozzle (A1/A2) is 5, what is: a. The velocity of the nozzle outlet, in [m/s], if the specific heat...
Question 1.4 A convergent-divergent nozzle is designed to operate with isentropic flow with an exit Mach number, Me. The flowin the nozzle is supplied from a reservoir of air with a static pressure ofPr and a static temperature of Tr and the nozzle has a throat area, AT, as specified in the table below Value Unit Design Data Exit Mach number (ME) 0.55 Area of throat (AT) 600 kPa Reservoir static pressure (PR) 380 WAT Reservoir static temperature (TR) kPa...
Can you please help me with part (e), thanks!
A B 72 Question 1.4 A convergent-divergent nozzle is designed to operate with isentropic flow with an exit Mach number, Me. The flow in the nozzle is supplied from a reservoir of air with a static pressure of PR and a static temperature of TR and the nozzle has a throat area, AT, as specified in the table below 73 Design Data Value Unit 75 Exit Mach number (ME) 76 77...
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...
5-1) (15) Estimate the exit pressure of the convergent-divergent nozzle for stable supersonic flow in the high-pressure turbine with the ratio of the exit area to the throat area of 1.1 with the throat diameter of 1cm and Get the exit steam velocity: (y = 1.4)
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...
Problem 2 was...
Air exapands in a frictionless adiabatic flow through a
converging-diverging nozzle at a mass flow rate of 2.5 kg/s. Source
stagnation condition are 1.1 Mpa and 115 C. If the nozzle exit
pressure is 141 kPa, and there are no shocks in the nozzle, find
the (a) the exit area Ae; (b) the throat At.
And I got (a) Ae = 1.11 * 10^(-3) m^2 and (b) At = 1.87 *
10^(-3) m^2
3. For the nozzle...
Air enters an isothermal nozzle at a temperature of 300 K, and a velocity of 10 m/s. The nozzle is very poorly insulated, causing a stray heat transfer rate of 10 kW into the system. The outlet of the nozzle is exposed to an ambient pressure of 1 bar and is choked (Mach = 1). If the area ratio of the nozzle (A, /A2) is 5, what is: The velocity of the nozzle outlet, in [m/s], if the specific heat...
2. Air enters an isothermal nozzle at a temperature of 300 K, and a velocity of 10 m/s. The nozzle is very poorly insulated, causing a stray heat transfer rate of 10 kW into the system. The outlet of the nozzle is exposed to an ambient pressure of 1 bar and is choked (Mach 1. If the area ratio of the nozzle (A1/A2) is 5, what is: a. The velocity of the nozzle outlet, in [m/s], if the specific heat...
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