![[15 pts] Consider a converging diverging nozzle with an exit-to-throat area ratio of Ae/At = 1.25 as shown below. The stagnat](http://img.homeworklib.com/questions/7e5efa70-f477-11eb-930f-ef3a9d340845.png?x-oss-process=image/resize,w_560)
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[15 pts] Consider a converging diverging nozzle with an exit-to-throat area ratio of Ae/At = 1.25...
Consider a converging-diverging nozzle with an exit-to-throat area ratio (Ae/At) of 5. The reservoir pressure (po)...
Consider a converging-diverging nozzle with an exit-to-throat area ratio (Ae/At) of 5. The reservoir pressure (po) and temperature (To) are equal to 5 atm and 600K, respectively. Determine exit Mach number, temperature and pressure values for normal shock at 3/4 of the diverging portion.
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...
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 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...
SP 7. The SpaceX Super Draco reaction control thrusters employ a converging-diverging nozzle to isentropically accelerate...
SP 7. The SpaceX Super Draco reaction control thrusters employ a converging-diverging nozzle to isentropically accelerate the flow of combusted monomethyl hydrazine/nitrogen tetroxide gases to supersonic speeds. The throat area in these engines is At = 0.0345 m2 https://internetprotocol.co/content/images/2020/01/Space-X.png a) Given that the pressure and temperature within the combustion chamber (where velocity 0) are po = 5 MPa and To = 3600 K, respectively, and that the flow exits the nozzle at an exit pressure, Pe 0.5 MPa , find...
1. (15 pts) A converging-diverging nozzle has an area ratio of 2, i.e., the exit (or duct) area is 2 times the throa...
1. (15 pts) A converging-diverging nozzle has an area ratio of 2, i.e., the exit (or duct) area is 2 times the throat area, which is 80 cm2. The nozzle is supplied from a tank containing air (y 1.4 and R 287 J/kg K) at 100 kPa and 300K. For both cases shown in Fig. , find the maximum mass flow possible through the nozzle and the range of back pressures over which the mass flow can be attained. For...
1. (15 pts) A converging-diverging nozzle has an area ratio of 2, i.e., the exit (or duct) area is 2 times the throa...
1. (15 pts) A converging-diverging nozzle has an area ratio of 2, i.e., the exit (or duct) area is 2 times the throat area, which is 80 cm2. The nozzle is supplied from a tank containing air (y 1.4 and R 287 J/kg K) at 100 kPa and 300K. For both cases shown in Fig. , find the maximum mass flow possible through the nozzle and the range of back pressures over which the mass flow can be attained. For...
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?
UBAV Air flows through a converging-diverging nozzle diffuser. A normal shock stands in the diverging section...
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:...
Throat area of 0.25m2 and exit to throat area ratio (Ae/At) of 35.5 are measured to be 1500 kPa a...
throat area of 0.25m2 and exit to throat area ratio (Ae/At) of 35.5 are measured to be 1500 kPa and 3000 K respectively. Assuming that the combustion product is steam ( 1.33, R 461.52 J/kg K), calculate the following: (e) The radius of the throat and exi plane of the nozde if the nozle has a circular cos- section. (b) The nozzle-exit plane conditions, i.e. Mach number, mass flow rate, velocity, pressure, าน temperature, and density. (c) The thrust and...
Consider a converging-diverging nozzle with an exit-to-throat area ratio (Ae/At) of 5. The reservoir pressure (po) and temperature (To) are equal to 5 atm and 600K, respectively. Determine exit Mach number, temperature and pressure values for normal shock at 3/4 of the diverging portion.
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...
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 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...
SP 7. The SpaceX Super Draco reaction control thrusters employ a converging-diverging nozzle to isentropically accelerate the flow of combusted monomethyl hydrazine/nitrogen tetroxide gases to supersonic speeds. The throat area in these engines is At = 0.0345 m2 https://internetprotocol.co/content/images/2020/01/Space-X.png a) Given that the pressure and temperature within the combustion chamber (where velocity 0) are po = 5 MPa and To = 3600 K, respectively, and that the flow exits the nozzle at an exit pressure, Pe 0.5 MPa , find...
1. (15 pts) A converging-diverging nozzle has an area ratio of 2, i.e., the exit (or duct) area is 2 times the throat area, which is 80 cm2. The nozzle is supplied from a tank containing air (y 1.4 and R 287 J/kg K) at 100 kPa and 300K. For both cases shown in Fig. , find the maximum mass flow possible through the nozzle and the range of back pressures over which the mass flow can be attained. For...
1. (15 pts) A converging-diverging nozzle has an area ratio of 2, i.e., the exit (or duct) area is 2 times the throat area, which is 80 cm2. The nozzle is supplied from a tank containing air (y 1.4 and R 287 J/kg K) at 100 kPa and 300K. For both cases shown in Fig. , find the maximum mass flow possible through the nozzle and the range of back pressures over which the mass flow can be attained. For...
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:...
throat area of 0.25m2 and exit to throat area ratio (Ae/At) of 35.5 are measured to be 1500 kPa and 3000 K respectively. Assuming that the combustion product is steam ( 1.33, R 461.52 J/kg K), calculate the following: (e) The radius of the throat and exi plane of the nozde if the nozle has a circular cos- section. (b) The nozzle-exit plane conditions, i.e. Mach number, mass flow rate, velocity, pressure, าน temperature, and density. (c) The thrust and...
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