Homework Answers
Add Answer to:
The Mach number at the throat of a nozzle with exit-to-throat area ratio of 2.637 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...
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.
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?
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...
[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...
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...
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...
Normal Shock Nozzle Exit (4, -6 cm? Back pressure Air from a reservoir at 350 K...
Normal Shock Nozzle Exit (4, -6 cm? Back pressure Air from a reservoir at 350 K and 500 kPa, flows through a converging-diverging nozzle. The throat area is 3 cm- and the exit area is 6 cm. A normal shock appears, for which the downstream (region 2) Mach number (M2) is 0.6405. Reservoir Throat (A = 3 cm (a) What is the Mach number (M]) upstream of the shock? 350K, 500 kPa (abs) (b) What is the area where the...
Normal Shock Nozzle Exit (4, -6 cm? Back pressure Air from a reservoir at 350 K...
Normal Shock Nozzle Exit (4, -6 cm? Back pressure Air from a reservoir at 350 K and 500 kPa, flows through a converging-diverging nozzle. The throat area is 3 cm- and the exit area is 6 cm. A normal shock appears, for which the downstream (region 2) Mach number (M2) is 0.6405. Reservoir Throat (A = 3 cm (a) What is the Mach number (M]) upstream of the shock? 350K, 500 kPa (abs) (b) What is the area where the...
Normal Shock Nozzle Exit (4, -6 cm? Back pressure Air from a reservoir at 350 K...
Normal Shock Nozzle Exit (4, -6 cm? Back pressure Air from a reservoir at 350 K and 500 kPa, flows through a converging-diverging nozzle. The throat area is 3 cm- and the exit area is 6 cm. A normal shock appears, for which the downstream (region 2) Mach number (M2) is 0.6405. Reservoir Throat (A = 3 cm (a) What is the Mach number (M]) upstream of the shock? 350K, 500 kPa (abs) (b) What is the area where the...
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.
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...
[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...
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...
Normal Shock Nozzle Exit (4, -6 cm? Back pressure Air from a reservoir at 350 K and 500 kPa, flows through a converging-diverging nozzle. The throat area is 3 cm- and the exit area is 6 cm. A normal shock appears, for which the downstream (region 2) Mach number (M2) is 0.6405. Reservoir Throat (A = 3 cm (a) What is the Mach number (M]) upstream of the shock? 350K, 500 kPa (abs) (b) What is the area where the...
Normal Shock Nozzle Exit (4, -6 cm? Back pressure Air from a reservoir at 350 K and 500 kPa, flows through a converging-diverging nozzle. The throat area is 3 cm- and the exit area is 6 cm. A normal shock appears, for which the downstream (region 2) Mach number (M2) is 0.6405. Reservoir Throat (A = 3 cm (a) What is the Mach number (M]) upstream of the shock? 350K, 500 kPa (abs) (b) What is the area where the...
Normal Shock Nozzle Exit (4, -6 cm? Back pressure Air from a reservoir at 350 K and 500 kPa, flows through a converging-diverging nozzle. The throat area is 3 cm- and the exit area is 6 cm. A normal shock appears, for which the downstream (region 2) Mach number (M2) is 0.6405. Reservoir Throat (A = 3 cm (a) What is the Mach number (M]) upstream of the shock? 350K, 500 kPa (abs) (b) What is the area where the...
Most questions answered within 3 hours.
-
In a survey of 1147 small-business owners, the following
question was posed: Would you recommend working...
asked 13 minutes ago -
The value of the equilibrium constant Kc for the reaction
N2(g)+3H2(g)⇌2NH3(g) changes in the following manner...
asked 20 minutes ago -
There are two flasks on the bench top, one flask contains a 0.50
M NaCl solution...
asked 25 minutes ago -
Which of the following aqueous solutions are good buffer
systems?
.
0.10 M hydrofluoric acid +...
asked 27 minutes ago -
2. An S election is terminated if the S corporation has passive
investment income in excess...
asked 29 minutes ago -
Part of an ANOVA table is shown below.
Source of
Variation
Sum of
Squares
Degrees of...
asked 45 minutes ago -
Business process improvement initiatives often include
introducing new technology to support the new or changed ways...
asked 52 minutes ago -
Review your choice of either Agile or the Waterfall models and
for each of the 22...
asked 53 minutes ago -
Suppose an x distribution has mean μ = 4.
Consider two corresponding
x
distributions, the first...
asked 55 minutes ago -
A study of the effects of exercise used rats bred to have high
or low capacity...
asked 1 hour ago -
Using your data from the experiment, calculate the initial moles
of HCl that you started with....
asked 1 hour ago -
Suppose you want to make 500 mL of a 0.20 M Tris buffer at pH
8.0....
asked 1 hour ago