a. Determine the length of the converging and diverging sections of the rocket nozzle by treating...
a. Determine the length of the converging and diverging sections of the rocket nozzle by treating the converging section as a cone and the diverging section as a parabola.
b. Find the throat radius, the combustion chamber radius and the nozzle exit radius.
Homework Answers
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a. Determine the length of the converging and diverging sections
of the rocket nozzle by treating...
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...
[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...
2. Air flows through a converging-diverging nozzle. There is a normal shock in the divergmy section...
2. Air flows through a converging-diverging nozzle. There is a normal shock in the divergmy section of the nozzle. The areas at throat, section 1. and section 2 are given in the figure below The sections 1 and 2 are located immediately upstream and downstream of the normal respectively. Therefore, the sections 1 and 2 are assumed to have the same area. There temperature and pressure are given as 300 K and 110 kPa, respectively. The entire isentropic except for...
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...
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...
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...
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.
This problem illustrates the effects of normal shock wave on an isentropic flow through a converging-diverging...
This problem illustrates the effects of normal shock wave on an isentropic flow through a converging-diverging nozzle. Air flows through an isentropic converging-diverging nozzle The air stagnation pressure and temperature are 7.0 x10 N/m2 and 500 K, respectively The diverging portion of the nozzle has an area ratio of AJA 13.0. A normal shock wave stands in the diverging section where the Mach number is 4.0. Analyze the case to caleulate the Mach number and the static temperature and pressure...
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...
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...
[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...
2. Air flows through a converging-diverging nozzle. There is a normal shock in the divergmy section of the nozzle. The areas at throat, section 1. and section 2 are given in the figure below The sections 1 and 2 are located immediately upstream and downstream of the normal respectively. Therefore, the sections 1 and 2 are assumed to have the same area. There temperature and pressure are given as 300 K and 110 kPa, respectively. The entire isentropic except for...
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...
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...
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.
This problem illustrates the effects of normal shock wave on an isentropic flow through a converging-diverging nozzle. Air flows through an isentropic converging-diverging nozzle The air stagnation pressure and temperature are 7.0 x10 N/m2 and 500 K, respectively The diverging portion of the nozzle has an area ratio of AJA 13.0. A normal shock wave stands in the diverging section where the Mach number is 4.0. Analyze the case to caleulate the Mach number and the static temperature and pressure...
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...
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