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?
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The throat area of a rocket nozzle is 5 cm2. The exit to throat
area ratio...
A certain ideal rocket with a nozzle are ratio of 2.3 and a throat area of...
A certain ideal rocket with a nozzle are ratio of 2.3 and a throat area of 5 sq. in. delivers gases at γ = 30 and R = 66 ft-lbf/lbm-⁰R at a chamber pressure of 300 psia and a constant chamber temperature of 5300 ⁰R against a back atmospheric pressure of 10 psia. By means of an appropriate valve arrangement, it is possible to throttle the propellant flow to the thrust chamber. Calculate and plot against pressure the following quantities...
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...
Consider the flow through a rocket engine nozzle. In the combustion chamber, the gas which results...
Consider the flow through a rocket engine nozzle. In the combustion chamber, the gas which results from the combustion of the rocket fuel and oxidizer is at a pressure and temperature of 15 atm and 2500K, respectively; the molecular weight and specific heat at constant pressure of the combustion gas are 12 kg/kmol and 4157 J/kg · K, respectively. Assume that the gas flow through the nozzle is an isentropic expansion of calorically perfect gas, with a temperature of 1350K...
[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...
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...
c) A nozzle in a wind tunnel gives a test-section Mach number of 2.0. Alr etes th nozzle from a large reservoir at 0,69 bar and 310 K. The cross-sectional area of the throat is 1000 cm2. Determine...
c) A nozzle in a wind tunnel gives a test-section Mach number of 2.0. Alr etes th nozzle from a large reservoir at 0,69 bar and 310 K. The cross-sectional area of the throat is 1000 cm2. Determine the following quantities for the tunnel for one dimensional isentropic flow i) Pressures, temperature and velocities at the throat and test sections, i) Area of cross-section of the test section, Sim) Mass flow rate, F rate required to drive the compressor
c)...
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...
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.
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.
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...
Consider the flow through a rocket engine nozzle. In the combustion chamber, the gas which results from the combustion of the rocket fuel and oxidizer is at a pressure and temperature of 15 atm and 2500K, respectively; the molecular weight and specific heat at constant pressure of the combustion gas are 12 kg/kmol and 4157 J/kg · K, respectively. Assume that the gas flow through the nozzle is an isentropic expansion of calorically perfect gas, with a temperature of 1350K...
[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...
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...
c) A nozzle in a wind tunnel gives a test-section Mach number of 2.0. Alr etes th nozzle from a large reservoir at 0,69 bar and 310 K. The cross-sectional area of the throat is 1000 cm2. Determine the following quantities for the tunnel for one dimensional isentropic flow i) Pressures, temperature and velocities at the throat and test sections, i) Area of cross-section of the test section, Sim) Mass flow rate, F rate required to drive the compressor
c)...
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...
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.
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