helium (k=1.6667) enters an ideal converging-diverging at a pressure of 73.5 psia of 1400F and negligible approach velocity. For isentropic expansion to an exit pressure of 14.7 psia, calculate the velocity of the helium leaving the nozzle in ft/s

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Q: At a point upstream of the throat in a conv.-div. nozzle, the velocity, pressure and temperature 242…

A: Stagnation propreties T01=T1+V22cp=315+15622*1.005*1000=327.1 K…

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Q: 48. Air enters a convergent-divergent nozzle at a temperature of 400K and a pressure of 10 atm. The…

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Q: A gas initially at a subsonic velocity enters an adiabatic diverging duct. Discuss how this affects…

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A: Effect of normal shock can on: Part (a): The velocity of fluid decreases with the application of…

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Q: 3- Mach number at a certain section in a diverging part of a c-d nozzle is 0.7. At farther section…

A: Given dataMach number at a certain section of a c-d nozzle = 0.7Mach number at exit Mexit = 0.4To…

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Q: A gas initially at a supersonic velocity enters an adiabatic converging duct. Discuss how this…

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Q: A gas at a specified stagnation temperature and pressure is accelerated to Ma = 2 in a…

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Q: A nozzle is said to be choked when...   oblique shock waves occur.   oblique expansion waves occur.…

A: Answer is (d) the maximum flow rate has been attained.

Q: Q1: Air at stagnation conditions of 2Mpa and 750K flows isentropic ally through a…

A: In Convergent diverging nozzles, hot gases exit the combustion chamber and narrow down smaller area.…

Q: Example 2 An air stream with a Mach number of (3.04) a pressure of (302 kPa) and a temperature of…

A:

Q: A gas initially at a supersonic velocity enters an adiabatic diverging duct. Discuss how this…

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Q: Calculate the stagnation temperature and pressure for the following substances flowing through a…

A: (a) Given, P=0.25 MPa, T= 50°C=323 K, velocity (V) =290 m/s Helium can be treated as an ideal gas,…

Q: 8. Air is flowing through a wide channel at a Mach number of 2 at a pressure of 140 kPa. The upper…

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Q: Air flows through a long, isentropic nozzle. The temp. and pressure at the reservoir are 1000 K and…

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Q: Air flowing steadily in a nozzle experiences a normal shock at a Mach number of Ma = 2.5. If the…

A: Given data P1=10 psiaT1=440.5 R

Q: Is it possible to accelerate a gas to a supersonic velocity in a converging nozzle? Explain

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Q: Prove that the total pressure is constant throughout an isentropic flow.

A: Answer : Isentropic Process : it is also known as reversible adiabatic process. In this process…

Q: Q.2. Air flows through a constant-area duct is connected to a reservoir at a temperature of 500°C…

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Q: Which of the following statement is FALSE? A In adiabatic compressible flow in a conduit of constant…

A: “Since you have posted a question with multiple subparts, we will solve first three sub parts for…

Q: Air at local pressure of 500 kPa and a local temperature of 400 K enters a frictionless, adiabatic…

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Q: The tunnel exhausts to the ambient environment, where the back pressure is Patm. The starting…

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Q: Helium enters a converging–diverging nozzle at 0.7 MPa, 800 K, and 100 m/s. What are the lowest…

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Q: Q9: A normal shock wave is propagated into still air with a velocity of 722.4 m/s. The still air…

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Q: Nitrogen is expanded isentropically in a nozzle from a pressure of 2000 kPa, at a temperature of…

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Q: Consider an equimolar mixture of oxygen and nitrogen. Determine the critical temperature, pressure,…

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Q: helium (k=1.6667) enters an ideal converging-diverging at a pressure of 73.5 psia of 1400F and…

A: Given data: Here, k represents the adiabatic constant, P1 represents the initial pressure, T1…

Q: 2. Air is supplied to a converging nozzle from a large reservoir where the temperature and pressure…

A:

Q: Air is flowing in a converging-diverging nozzle with an expansion ratio of 10. The inlet stagnation…

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Q: Nitrogen enters a converging–diverging nozzle at 620 kPa and 310 K with a negligible velocity, and…

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Q: A large tank supplies helium through a converging-diverging nozzle to the atmosphere. Pressure in…

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Q: Q.1. A uniform supersonic air flow travelling at a Mach number of 2.5 passes over a wedge which…

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Q: Helium enters a converging–diverging nozzle at 500 kPa, 450 °C, and 550 km/h. Calculate the lowest…

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A: Write the expression of oblique shock angle. tanθ=2Ma12sin2β-1/tanβMa12k+cos2β+2

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A: Assume,  P0=200 kPaT0=500 KP*=528 P0=105.7 kPaT*=T01.2=416.6 Kρ*=P*RT*=105.7×103287×416.6=0.884…