The converging nozzle has an exit diameter of 0.25 m.The fuel-oxidizer mixture within the large tank has anabsolute pressure of 4 MPa and temperature of1500 K. The mixture has k = 1.38 andR = 296 J/kg-K]. (Figure 1)Figure0.25 mF1 of 1Part ADetermine the mass flow from the nozzle when the backpressure is a vacuum.Express your answer using three significant figures.VE| ΑΣΦ | 11 | vecm=SubmitProvide FeedbackRequest Answer?kg/sNext >

Answered: Image /qna-images/answer/90da0490-917e-46db-9e7b-d1ba9f221a92.jpg

Answered: The converging nozzle has an exit…

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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Nitrogen enters a converging–diverging nozzle at 800 kPa and 400 K with a negligible velocity. Determine the critical velocity, pressure, temperature, and density in the nozzle. Use data from the tables. The properties of nitrogen are k = 1.4 and R = 0.2968 kJ/kg·K
Air at a temperature of 20°C and standard atmospheric pressure of 102 kPa flows through the nozzle into the pipe where the absolute internal pressure is 60 kPa. The nozzle has a throat diameter of d = 11 mm. (Figure 1) Figure 1 of 1 Part A Determine the mass flow into the pipe. Express your answer using three significant figures. ΤΙ ΑΣΦ ↓↑ vec m = Submit Provide Feedback Request Answer ? g/s
The large tank contains air at an absolute pressure of 80 psi and temperature of 70°F. The nozzle has a throat diameter of 1 in. and an exit diameter of 1.75 in. (Figure 1) Part A T = °R. Part B Determine the absolute pressure within the connected pipe so that the nozzle chokes, but also maintains isentropic subsonic flow within the divergent section of the nozzle. Express your answer using three significant figures. p = psi Part C Determine the mass flow into the tank if the absolute pressure within the pipe is 30 psi. Express your answer using three significant figures. m = slug/s
During the entry of the space shuttle into the earth’s atmosphere, maximum stagnation point heating occurs at the trajectory point corresponding to an altitude of 68.9 km, where ρ∞ = 1.075 × 10−4 kg/m3, and a flight velocity of 6.61 km/s. At this point on its entry trajectory, the shuttle is at a 40.2 degree angle of attack, which presents an effective nose radius at the stagnation point of 1.29 m. If the wall temperature is Tw = 1110 K, calculatethe stagnation point heating rate.
Quick -sol
A converging nozzle with an exit diameter of 6 cm is attached to a reservoir maintained at 30 degrees C and 150 kPa absolute. Determine the mass flux of air flowing through the nozzle if the receiver exits to the atmosphere. Use applicable equations. Express in kg/s snd in 3 decimal places.
The large cylindrical tank contains air at an absolute pressure of 200 psi and temperature of 90°F. The throat of the nozzle has a diameter of 0.25 in., and the exit diameter is 0.75 in. (Figure 1) Part A Determine the absolute pressure in the pipe required to choke the nozzle and also maintain isentropic subsonic flow through the pipe. Express your answer using four significant figures. p= psi Part B What is the velocity of the flow through the pipe for this condition? Express your answer to three significant figures and include the appropriate units. V = Value Units
There is 7kg of steam having pressure of 200kPa. Determine the flow energy per unit mass, specific enthalpy, total enthalpy.
Problem 3 – Sparky needs helium for an experimental project. The helium is stored in a storage tank at 20°C and 300 kPa. The helium exits through a converging nozzle to the environment (100 kPa atmospheric pressure) and has 10 mm exit diameter. Determine the exit flow rate of the helium. Helium’s ratio of specific heats is 1.667. This is a compressible flow problem. Only use equations and tables from the textbook to solve this problem. Note the figures in the textbook and textbook appendices are based in air, not helium, and are not valid for this problem.

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