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5-1) (15) Estimate the exit pressure of the convergent-divergent nozzle for stable supersonic flow in 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...
1. Which of the following is not true for steam nozzles? a. In convergent nozzle there...
1. Which of the following is not true for steam nozzles? a. In convergent nozzle there is divergent after throat b. Convergent-divergent nozzle has higher expansion ratio c. Convergent-divergent nozzle produces steam at higher velocities as compared to a convergent nozzle d. All of the above 2. The steam turbine can be governed by the following methods except a. Throttle governing b. Nozzle governing c. By pass governing d. Reaction governing 3. Which of the following is a steam turbine?...
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...
B. Consider the flow of air through a convergent-divergent duct, with inlet, throat and exit areas...
B. Consider the flow of air through a convergent-divergent duct, with inlet, throat and exit areas are 6, 4 and 5 m2, respectively. The inlet and exit pressure are 1.01X105 N/m2 and 1X105 N/m2, respectively. Calculate the flow velocity at the inlet, throat and exit. (assume incompressible flow with standard sea-level density). Throat p. P. V
(a) A supersonic nozzle is attached to a constant diameter circular duct at its exit The...
(a) A supersonic nozzle is attached to a constant diameter circular duct at its exit The duct diameter is the same as the nozzle exit diameter. Nozzle exit cross section area is three times that of its throat. The gas (k-14, R 287 Jg K) enters the nozzle with pressure and temperature of 10 bar and 600 Krespectively with negligible velocity. If a normal shock occurs at a section in the diverging part of the nozzle where the area ratio...
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...
B4 (a) Ste the parameter that is normally used to differentiate between incompressible and compressible flow conditions. What value is normally chosen for this parameter to signify a change from one...
B4 (a) Ste the parameter that is normally used to differentiate between incompressible and compressible flow conditions. What value is normally chosen for this parameter to signify a change from one condition to another? (5%] For isentropic flow conditions, sketch a subsonic and a supersonic nozzle (b) Sketch also a subsonic and a supersonic diffuser. [1096] (c) A converging-diverging nozzle is attached at one end to a large supply tank that contains air, and at the other end to a...
[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...
Air at a local pressure of 650 kpa and local temperature of 280 K enter a...
Air at a local pressure of 650 kpa and local temperature of 280 K enter a frictinless adiabatic convergent- Divergent nozzle with velocity of 160m/s. the throat area of nozzle is 3.2cm^2 and the exit area is 14cm^2 and the shock occurs where the nozzle area is 8cm^2 fined the following: 1- Back pressure. 2- The flow velocity on both side of the shock. 3-What is the flow rate. 4- Exit Mach number. 5- Mach number on both side of...
Question 4 Soalan 4] (a) A supersonic nozzle is attached to a constant diameter circular duct...
Question 4 Soalan 4] (a) A supersonic nozzle is attached to a constant diameter circular duct at its exit The duct diameter is the same as the nozzle exit diameter. Nozzle exit cross- section area is three times that of its throat. The gas (k1.4, R = 287 J/kg-K ) enters the nozzle with pressure and temperature of 10 bar and 600 K respectively with negligible velocity. If a normal shock occurs at a section in the diverging part of...
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...
B. Consider the flow of air through a convergent-divergent duct, with inlet, throat and exit areas are 6, 4 and 5 m2, respectively. The inlet and exit pressure are 1.01X105 N/m2 and 1X105 N/m2, respectively. Calculate the flow velocity at the inlet, throat and exit. (assume incompressible flow with standard sea-level density). Throat p. P. V
(a) A supersonic nozzle is attached to a constant diameter circular duct at its exit The duct diameter is the same as the nozzle exit diameter. Nozzle exit cross section area is three times that of its throat. The gas (k-14, R 287 Jg K) enters the nozzle with pressure and temperature of 10 bar and 600 Krespectively with negligible velocity. If a normal shock occurs at a section in the diverging part of the nozzle where the area ratio...
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...
B4 (a) Ste the parameter that is normally used to differentiate between incompressible and compressible flow conditions. What value is normally chosen for this parameter to signify a change from one condition to another? (5%] For isentropic flow conditions, sketch a subsonic and a supersonic nozzle (b) Sketch also a subsonic and a supersonic diffuser. [1096] (c) A converging-diverging nozzle is attached at one end to a large supply tank that contains air, and at the other end to a...
[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...
Question 4 Soalan 4] (a) A supersonic nozzle is attached to a constant diameter circular duct at its exit The duct diameter is the same as the nozzle exit diameter. Nozzle exit cross- section area is three times that of its throat. The gas (k1.4, R = 287 J/kg-K ) enters the nozzle with pressure and temperature of 10 bar and 600 K respectively with negligible velocity. If a normal shock occurs at a section in the diverging part of...
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