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Air enters an approximately frictionless duct with \(V_{1}=70 \mathrm{m} / \mathrm{s}, T_{1}=600 \mathrm{K},\) and \(P_{1}=350\) kPa. Letting the exit temperature \(T_{2}\) vary from 600 to 5000 \(\mathrm{K},\) evaluate the entropy change at intervals of \(200 \mathrm{K},\) and plot the Rayleigh line on a \(T\) -s diagram.

Short Answer

Expert verified
Question: Calculate the change in entropy of air inside a frictionless duct for different exit temperatures and plot the Rayleigh line on a T-s diagram. Given the initial velocity \(V_1 = 70~m/s\), initial temperature \(T_1 = 600~K\), initial pressure \(P_1 = 350~kPa\) and exit temperature range from \(600~K\) to \(5000~K\) with intervals of \(200~K\). Answer: To find the change in entropy, we used the isentropic relations and calculated \(\Delta s\) for each exit temperature in the given range and intervals. Then, we plotted the Rayleigh line on a T-s diagram to represent the relationship between exit temperature and entropy change.

Step by step solution

01

Understand the given data

The given data in the problem are: Initial velocity: \(V_1 = 70~m/s\) Initial temperature: \(T_1 = 600~K\) Initial pressure: \(P_1 = 350~kPa\) Exit temperature: \(T_2\) varying from \(600~K\) to \(5000~K\) with intervals of \(200~K\)
02

Calculate entropy change

To find the entropy change for each exit temperature \(T_2\) in the given range, we can use the following isentropic relation between temperature, pressure, and specific heat ratios: $$\frac{T_2}{T_1} = \left(\frac{P_2}{P_1}\right)^\frac{\gamma - 1}{\gamma}$$ Where \(\gamma\) is the specific heat ratio, which for air is approximately \(1.4\). We can rearrange this equation to solve for \(P_2\) and substitute \(P_1\) and \(T_1\) values: $$P_2 = P_1 \left(\frac{T_2}{T_1}\right)^\frac{\gamma}{\gamma-1}$$ Now, we calculate the entropy change as follows: $$\Delta s = c_p \ln\frac{T_2}{T_1} - R \ln\frac{P_2}{P_1}$$ Where \(c_p\) is the specific heat at constant pressure and \(R\) is the specific gas constant. For air, \(c_p = 1.005~kJ/(kg~K)\) and \(R = 0.287~kJ/(kg~K)\). Now, calculate the entropy change \(\Delta s\) for each exit temperature \(T_2\) in the given range and intervals.
03

Plot the Rayleigh line

Using the calculated values of entropy change and exit temperature, plot the Rayleigh line on a T-s diagram. This plot represents the relation between the exit temperature \(T_2\) and entropy change \(\Delta s\). In conclusion, to solve this exercise, we have derived the isentropic relation to find the entropy change for different exit temperatures. We have calculated the entropy change for each given exit temperature in the specified range and intervals. Finally, we plotted the Rayleigh line on a T-s diagram to represent the relationship between exit temperature and entropy change.

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Most popular questions from this chapter

Air enters a converging-diverging nozzle of a supersonic wind tunnel at \(1 \mathrm{MPa}\) and \(300 \mathrm{K}\) with a low velocity. If a normal shock wave occurs at the exit plane of the nozzle at \(\mathrm{Ma}=2.4,\) determine the pressure, temperature, Mach number, velocity, and stagnation pressure after the shock wave.

Design a 1-m-long cylindrical wind tunnel whose diameter is \(25 \mathrm{cm}\) operating at a Mach number of \(1.8 .\) Atmospheric air enters the wind tunnel through a converging- diverging nozzle where it is accelerated to supersonic velocities. Air leaves the tunnel through a converging-diverging diffuser where it is decelerated to a very low velocity before entering the fan section. Disregard any irreversibilities. Specify the temperatures and pressures at several locations as well as the mass flow rate of air at steady- flow conditions. Why is it often necessary to dehumidify the air before it enters the wind tunnel?

Consider subsonic Rayleigh flow of air with a Mach number of \(0.92 .\) Heat is now transferred to the fluid and the Mach number increases to \(0.95 .\) Does the temperature \(T\) of the fluid increase, decrease, or remain constant during this process? How about the stagnation temperature \(T_{0} ?\) 17-102C What is the characteristic aspect of Rayleigh flow? What are the main assumptions associated with Rayleigh flow?

Using EES (or other) software, determine the shape of a converging-diverging nozzle for air for a mass flow rate of \(3 \mathrm{kg} / \mathrm{s}\) and inlet stagnation conditions of \(1400 \mathrm{kPa}\) and \(200^{\circ} \mathrm{C}\). Approximate the flow as isentropic. Repeat the calculations for 50 -kPa increments of pressure drop to an exit pressure of \(100 \mathrm{kPa}\). Plot the nozzle to scale. Also, calculate and plot the Mach number along the nozzle.

Consider subsonic Rayleigh flow that is accelerated to sonic velocity \((\mathrm{Ma}=1)\) at the duct exit by heating. If the fluid continues to be heated, will the flow at duct exit be supersonic, subsonic, or remain sonic?

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