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 >

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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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A converging nozzle having an exit diameter of 30 mmmm is connected to the large tank (Figure 1). The absolute pressure outside the tank is 102 kPakPa. If the temperature of the air in the tank is 20∘C∘C and the absolute pressure is 480 kPakPa, determine the mass flow from the tank. Express your answer using three significant figures.
The large tank contains air at an absolute pressure of 700 kPa and temperature of 400 K. The converging nozzle between the tank and the pipe has an exit diameter of 40 mm and the absolute pressure in the pipe is 150 kPa. For air R = 286.9 J/[kg · K] and k = 1.40. (Figure 1) Determine the mass flow from the tank the pipe. Express your answer using three significant figures. m = kg/s
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
Air flows through a long, isentropic nozzle. The temperature and pressure at the * reservoir are 1000K and 20 atm, respectively. If the Mach number at the entrance is 0.2, determine the gas velocity at the entrance. 634 m/s 127 m/s 478 m/s 254 m/s For a large centrifugal pump, the required net positive suction head is typically around 5 ft 2 ft 15 ft
Derive an expression for the speed of sound based on van der Waals’ equation of state P = RT(v − b) − a/v2. Using this relation, determine the speed of sound in carbon dioxide at 80°C and 320 kPa, and compare your result to that obtained by assuming ideal-gas behavior. The van der Waals constants for carbon dioxide are a = 364.3 kPa·m6/kmol2 and b = 0.0427 m3/kmol.
Hot gas enters the turbine at a pressure of 600kPa and a temperature of 1200K at a speed of 60m / s and exits at a pressure of 300kPa and a speed of 70m / s with a cross-sectional area of 0.125m ^ 2. Assume isotropic and constant flow and hot gas as a complete gas with a molar mass of 25kg / kmol and γ = 1.35 turbine power.
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.
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.
1- Air enters a nozzle at 0.2 MPa, 350 K, and a stagnation velocity. Assuming isentropic flow, determine the pressure and temperature of air at a location where the air velocity equals the speed of sound. What is the ratio of the area at this location to the entrance area?
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

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