A converging duct is fed with air from a large reservoir where the temperature and pressure are 400 K and 200 kPa, respectively. The Mach number at a point along the duct, where the cross•sectional area is 0.01 m', is 0.7. Determine the temperature, pressure, velocity and density at that point, and also calculate the mass flow rate. Assume lsentropic flow throughout the nozzle.

Q: Q3) A convergent-divergent nozzle has a cross-sectional area at the throat of 0.1 m² Air enters the…

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Q: . Air is flowing isentropically through a converging duct which is fed from a large where the…

A: Since you have asked multiple questions in a single request, we would be answering only the first…

Q: Q3) A convergent-divergent nozzle has a cross-sectional area at the throat of 0.1 m² Air enters the…

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Q: How does the normal shock affect (a) the fluid velocity, (b) the static temperature, (c) the…

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Q: Air at 200 kPa, 100 °C, and Mach number Ma=0.8 flows through a duct. Calculate thevelocity, the…

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Q: A convergent-divergent nozzle with an exit-to-throat area ratio of 1.616has exit and reservoir…

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Q: Air flows from a large tank where the pressure and temperature are 600 kPa and 800 K, respectively,…

A: P1=600 KpaT1=800KA2=.0005 m2P2= 100 Kpa T2T1=P2P1γ-1γT2800=1006001.4-11.4T2=479.4695 K

Q: 1. Air is flowing isentropically through a converging duct which is fed from a large temperature and…

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Q: A converging–diverging nozzle receives air from a tank at 100 psia and 600°R. The pressure is 28.0…

A: Dear student as per the policy i have solved first three subparts for you please post the…

Q: Nitrogen enters a duct with varying flow area at 400 K, 100 kPa, and a Mach number of 0.3. Assuming…

A: Given data as per question intitial temperature = 400 k initial pressure = 100 kpa Mach no. = 0.3…

Q: 4- Air at stagnation pressure of 600 kpa and stagnation temperature of 530 K enters a frictionless…

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Q: 1. Air flow isentropically through a converging nozzle attached to a reservoir, where the pressure…

A: Given data P0=170 KPaT0=300 KM=0.2

Q: · Air is flowing isentropically through a converging duct which is fed from a large reservoir where…

A: T1=350 K,P1=250 kPaAC=.005 m2 ,P2=150 kPa T2T1=P2P1γ-1γT2350=1502501.4-11.4T2=302.47 KNow for…

Q: 1. Air is flowing isentropically through a converging duct which is fed from a large reservoir where…

A: We are suppose to solve only one question. Please post other question as a separate question.

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: Q.2 Air which enters a diverging duct is slowed by a normal shock wave, as shown in figure. The…

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Q: An aircraft flies with a Mach number Ma1 = 0.9 at an altitude of 7000 m where the pressure is 41.1…

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Q: An air nozzle has an exit area 1.6 times the throat area. If a normal shock occurs at a plane where…

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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: A converging -diverging nozzle with a throat area of 0.0052 m^2 is attached to a very large tank of…

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

A: We have a standard equation, dAA=dpρV21-M2 The above equation is both for nozzle and diffuser, For a…

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

A: Stagnation point: The point at which the velocity of the fluid becomes zero. When the fluid is…

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

A: Given data: The inlet temperature is T1=500 °C. The inlet Pressure is P1=500 kPa The heat loss rate…

Q: A centrifugal compressor has an impeller tip speed of 360 m/s. Determine the absolute Mach number of…

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

A: Given, P1=500KPa T1=400K V1=140m/s Throat area, Ax*=2.5 cm2Exit area, Ae=10 cm2Nozzle area where…

Q: Q4: A convergent-divergent nozzle is operating under off-design conditions resulting in the presence…

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Q: Nitrogen enters a duct with varying flow area at 400 K, 100 kPa, and a Mach number of 0.5. Assuming…

A: Given data: The temperature at the inlet of the duct, T1 = 400 K. The pressure at the inlet of the…

Q: An ideal isentropic nozzle is attached to an infinite reservoir that has stagnation conditions 3 MPa…

A: For solution refer below images.

Q: 4- Air at stagnation pressure of 600 kpa and stagnation temperature of 530 K enters a frictionless…

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Q: Consider a normal shock wave in a supersonic airstream where the pressure upstream of the shock is 1…

A: Given data: Initial upstream pressure, P1 = 1 atm. From the standard air properties, the specific…

Q: Air is flowing isentropically through a converging duct which is fed from a large reservoir where…

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

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Q: The Mach number at the exit is ●●●●●●● Air at stagnation pressure of 600 kpa and stagnation…

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Q: Q.1. Air flow adiabatically in a constant area duct. At the inlet of the duct, the Mach number,…

A: Given Data : At Inlet Mach Number Mi = 0.6 Pressure Pi = 150 KPa Temperature Ti =300 K Duct Length…

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Q: Is it possible to accelerate a fluid to supersonic velocities with a velocity other than the sonic…

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Q: Consider a normal shock wave in a supersonic airstream where the pressure upstream of the shock is 1…

A: Data given-  p01 = 1 atm M1 = 2.5  M1 = 4.5

Q: Nitrogen enters a converging–diverging nozzle at 700 kPa and 400 K with a negligible velocity.…

A: Given data as per the question The pressure of nitrogen =700kpa Temperature =400 k…

Q: Consider subsonic Fanno flow of air with an inlet Mach number of 0.70. If the Mach number increases…

A: (a) The stagnation temperature during the Fanno flow process remains constant because the heat and…

Q: Consider the isentropic flow through a convergent-divergent nozzle with an exit-to-throat area ratio…

A: Given data Convergent - Divergent. exit Throat = 2.5 a)  P = 1 atm     T = 2881 Find: Mach number…

Q: Air is expanded from 200 kPa and 500°K through a throat to an exit Mach number of 2.5. If the…

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…

Q: A stationary normal shock occurs in an air stream when the pressure, temperature and Mach number are…

A: Step 1

Q: Air enters a rectangular duct at T₁ = 300 K, P₁ = = 420 kPa, and Ma₁ = 2. Heat is transferred to the…

A: Given data as per question  T₁ = 300 K P₁ = = 420 kPa  Ma₁ = 2 Heat is transferred to the air =55…

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Entropy

In physics, entropy means the amount of disorder or the degree of randomness associated with a thermodynamic system. The system is not self-organized when the entropy of the system is high. For instance, when a system is at an elevated temperature, its molecules are in random motion, vibrating and colliding with each other. During this scenario, the probability of finding a molecule at a particular place twice, is low. Under this circumstance, the system can be said to be in a high entropy.