/*! This file is auto-generated */ .wp-block-button__link{color:#fff;background-color:#32373c;border-radius:9999px;box-shadow:none;text-decoration:none;padding:calc(.667em + 2px) calc(1.333em + 2px);font-size:1.125em}.wp-block-file__button{background:#32373c;color:#fff;text-decoration:none} Problem 100 A cylinder of \(30-\mathrm{mm}\)... [FREE SOLUTION] | 91Ó°ÊÓ

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A cylinder of \(30-\mathrm{mm}\) diameter and \(150-\mathrm{mm}\) length is heated in a large furnace having walls at \(1000 \mathrm{~K}\), while air at \(400 \mathrm{~K}\) is circulating at \(3 \mathrm{~m} / \mathrm{s}\). Estimate the steady-state cylinder temperature under the following specified conditions. (a) The cylinder is in cross flow, and its surface is diffuse and gray with an emissivity of \(0.5\). (b) The cylinder is in cross flow, but its surface is spectrally selective with \(\alpha_{\lambda}=0.1\) for \(\lambda \leq 3 \mu \mathrm{m}\) and \(\alpha_{\lambda}=0.5\) for \(\lambda>3 \mu \mathrm{m}\). (c) The cylinder surface is positioned such that the airflow is longitudinal and its surface is diffuse and gray. (d) For the conditions of part (a), compute and plot the cylinder temperature as a function of the air velocity for \(1 \leq V \leq 20 \mathrm{~m} / \mathrm{s}\).

Short Answer

Expert verified
(a) Steady-state cylinder temperature for cross flow with gray surface: \(T_{cylinder} = f(Q_{total_a})\) (b) Steady-state cylinder temperature for cross flow with spectrally selective surface: \(T_{cylinder} = f(Q_{total_b})\) (c) Steady-state cylinder temperature for longitudinal flow with gray surface: \(T_{cylinder} = f(Q_{total_c})\) (d) Plot the steady-state cylinder temperature as a function of air velocity for 1 to 20 m/s, for cross flow with gray surface.

Step by step solution

01

Calculate Convection Heat Transfer Coefficient

To determine the convection heat transfer coefficient (h), we can use the Nu-Ra correlation formula: \(Nu = KaRa^x\) Where Nu is the Nusselt number, Ka is a constant depending on geometry, and Ra is the Rayleigh number. Given that air is at 3 m/s velocity, we use a suitable correlation for calculating h directly for a cylinder in cross-flow, like the Hilpert correlation.
02

Calculate Radiation Heat Transfer Rate

To calculate radiation heat transfer, we use the Stefan-Boltzmann Law, considering emissivity and wall temperatures. \(Q_{rad}=εσA(T_{wall}^4-T_{cylinder}^4)\) For the given conditions, we can calculate \(Q_{rad}\) separately. In case (b), we will separate the spectral ranges for \(λ\leq3μm\) and \(λ>3μm\) and sum their contributions.
03

Calculate Total Heat Transfer Rate

Now, we can calculate the total heat transfer rate considering convection and radiation: \(Q_{total}=Q_{conv}+Q_{rad}\) The convection heat transfer rate can be found using \(Q_{conv}=hA(T_{air}-T_{cylinder})\). Calculate the total heat transfer rate for each case (a, b, and c).
04

Estimate Steady-state Cylinder Temperature

When the cylinder reaches steady-state, the total heat transfer rate equals the heat absorbed by the cylinder. Therefore, we can find the temperature of the cylinder, considering these heat transfer rates. Solve the following equations for each case: - Part (a): \(T_{cylinder} = f(Q_{total_a})\) - Part (b): \(T_{cylinder} = f(Q_{total_b})\) - Part (c): \(T_{cylinder} = f(Q_{total_c})\)
05

Compute and Plot Cylinder Temperature (Part d)

For part (d), we need to compute and plot the cylinder temperature as a function of the air velocity for 1 to 20 m/s. Modify the calculation for convection heat transfer coefficient according to the velocity. Then, follow Steps 2, 3, and 4 for each velocity value and plot the resulting relationship between cylinder temperature and air velocity.

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Key Concepts

These are the key concepts you need to understand to accurately answer the question.

Convection Heat Transfer
Convection heat transfer refers to the process of heat being transported between a solid surface and a fluid, such as air or water, that is in motion. This is particularly important in systems like our case where air flows over a heated cylinder. The convection heat transfer coefficient, denoted as \( h \), depends on various factors such as the fluid's properties, flow velocity, and specific geometry of the surface. In the solution, we are dealing with a cylinder in cross-flow with air moving across it at a speed of 3 m/s. To calculate \( h \), we often use empirical correlations like the Hilpert correlation, which is suitable for calculating the coefficient directly based on known parameters. Remember, the convection heat transfer rate, \( Q_{conv} \), can be determined using the formula:\[ Q_{conv} = h \cdot A \cdot (T_{air} - T_{cylinder}) \]Here, \( A \) stands for the surface area of the cylinder, \( T_{air} \) is the temperature of the surrounding air, and \( T_{cylinder} \) is the temperature of the cylinder itself. It's important to correctly identify these values to ensure an accurate solution.
Radiation Heat Transfer
Radiation heat transfer occurs through electromagnetic waves and is significant when dealing with high-temperature environments, such as the heated cylinder in a furnace. It involves energy being emitted by surfaces due to their temperature. A key principle in calculating radiation heat transfer is the Stefan-Boltzmann law, which relates the power radiated by a body to its absolute temperature:\[ Q_{rad} = \varepsilon \sigma A (T_{wall}^4 - T_{cylinder}^4) \]Here, \( \varepsilon \) is the emissivity of the surface, \( \sigma \) is the Stefan-Boltzmann constant, \( A \) is the area, and \( T_{wall} \) and \( T_{cylinder} \) are the temperatures of the furnace walls and the cylinder, respectively. In situations where the surface is diffuse (even emission across all directions) and gray (constant emissivity across all wavelengths), the calculations remain straightforward. For spectrally selective surfaces, however, it’s necessary to consider different emissivity values for different wavelength ranges, as seen in case (b) of our exercise. Here, radiation is calculated separately for wavelengths \( \lambda \leq 3 \mu \text{m} \) and \( \lambda > 3 \mu \text{m} \) based on varying values of emissivity. Understanding these subtleties allows for accurate predictions and control over the heat distribution and temperature within a thermal system.
Nusselt Number
The Nusselt number, \( Nu \), is a dimensionless parameter that provides a measure of the convection heat transfer rate relative to the conductive heat transfer rate. It plays a crucial role in scaling the heat transfer processes, especially in convection scenarios like the cylindrical heating in the exercise.Mathematically, it is often expressed in terms of relevant parameters such as the Rayleigh number (\( Ra \)) and a geometry-dependent constant (\( Ka \)) in correlations like \( Nu = KaRa^x \). For cylinder in a cross-flow scenario, the Nusselt number can help estimate the heat transfer coefficient, \( h \), by using empirical data and correlations like the Hilpert correlation, simplifying the complex relationship between the flow characteristics and heat transfer. Understanding the Nusselt number allows you to deepen your insight into how geometry and flow conditions affect heat transfer rates.By determining \( Nu \), we can compare the efficiency of heat transfer in different systems or conditions, making it a valuable tool not only for analysis but also for the design and optimization of thermal systems.

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Most popular questions from this chapter

A furnace with an aperture of 20 -mm diameter and emissive power of \(3.72 \times 10^{5} \mathrm{~W} / \mathrm{m}^{2}\) is used to calibrate a heat flux gage having a sensitive area of \(1.6 \times 10^{-5} \mathrm{~m}^{2}\). (a) At what distance, measured along a normal from the aperture, should the gage be positioned to receive irradiation of \(1000 \mathrm{~W} / \mathrm{m}^{2}\) ? (b) If the gage is tilted off normal by \(20^{\circ}\), what will be its irradiation? (c) For tilt angles of 0,20 , and \(60^{\circ}\), plot the gage irradiation as a function of the separation distance for values ranging from 100 to \(300 \mathrm{~mm}\).

A circular metal disk having a diameter of \(0.4 \mathrm{~m}\) is placed firmly against the ground in a barren horizontal region where the earth is at a temperature of \(280 \mathrm{~K}\). The effective sky temperature is also \(280 \mathrm{~K}\). The disk is exposed to quiescent ambient air at \(300 \mathrm{~K}\) and direct solar irradiation of \(745 \mathrm{~W} / \mathrm{m}^{2}\). The surface of the disk is diffuse with \(\varepsilon_{\lambda}=0.9\) for \(0<\lambda<1 \mu \mathrm{m}\) and \(\varepsilon_{\lambda}=0.2\) for \(\lambda>1 \mu \mathrm{m}\). After some time has elapsed, the disk achieves a uniform, steady-state temperature. The thermal conductivity of the soil is \(0.52 \mathrm{~W} / \mathrm{m} \cdot \mathrm{K}\). (a) Determine the fraction of the incident solar irradiation that is absorbed. (b) What is the emissivity of the disk surface? (c) For a steady-state disk temperature of \(340 \mathrm{~K}\), employ a suitable correlation to determine the average free convection heat transfer coefficient at the upper surface of the disk. (d) Show that a disk temperature of \(340 \mathrm{~K}\) does indeed yield a steady-state condition for the disk.

A furnace with a long, isothermal, graphite tube of diameter \(D=12.5 \mathrm{~mm}\) is maintained at \(T_{f}=2000 \mathrm{~K}\) and is used as a blackbody source to calibrate heat flux gages. Traditional heat flux gages are constructed as blackened thin films with thermopiles to indicate the temperature change caused by absorption of the incident radiant power over the entire spectrum. The traditional gage of interest has a sensitive area of \(5 \mathrm{~mm}^{2}\) and is mounted coaxial with the furnace centerline, but positioned at a distance of \(L=60 \mathrm{~mm}\) from the beginning of the heated section. The cool extension tube serves to shield the gage from extraneous radiation sources and to contain the inert gas required to prevent rapid oxidation of the graphite tube. (a) Calculate the heat flux \(\left(\mathrm{W} / \mathrm{m}^{2}\right)\) on the traditional gage for this condition, assuming that the extension tube is cold relative to the furnace. (b) The traditional gage is replaced by a solid-state (photoconductive) heat flux gage of the same area, but sensitive only to the spectral region between \(0.4\) and \(2.5 \mu \mathrm{m}\). Calculate the radiant heat flux incident on the solid-state gage within the prescribed spectral region. (c) Calculate and plot the total heat flux and the heat flux in the prescribed spectral region for the solidstate gage as a function of furnace temperature for the range \(2000 \leq T_{f} \leq 3000 \mathrm{~K}\). Which gage will have an output signal that is more sensitive to changes in the furnace temperature?

Two plates, one with a black painted surface and the other with a special coating (chemically oxidized copper) are in earth orbit and are exposed to solar radiation. The solar rays make an angle of \(30^{\circ}\) with the normal to the plate. Estimate the equilibrium temperature of each plate assuming they are diffuse and that the solar flux is \(1368 \mathrm{~W} / \mathrm{m}^{2}\). The spectral absorptivity of the black painted surface can be approximated by \(\alpha_{\lambda}=0.95\) for \(0 \leq \lambda \leq \infty\) and that of the special coating by \(\alpha_{\lambda}=0.95\) for \(0 \leq \lambda<3 \mu \mathrm{m}\) and \(\alpha_{\lambda}=0.05\) for \(\lambda \geq 3 \mu \mathrm{m}\).

The oxidized-aluminum wing of an aircraft has a chord length of \(L_{c}=4 \mathrm{~m}\) and a spectral, hemispherical emissivity characterized by the following distribution. (a) Consider conditions for which the plane is on the ground where the air temperature is \(27^{\circ} \mathrm{C}\), the solar irradiation is \(800 \mathrm{~W} / \mathrm{m}^{2}\), and the effective sky temperature is \(270 \mathrm{~K}\). If the air is quiescent, what is the temperature of the top surface of the wing? The wing may be approximated as a horizontal, flat plate. (b) When the aircraft is flying at an elevation of approximately \(9000 \mathrm{~m}\) and a speed of \(200 \mathrm{~m} / \mathrm{s}\), the air temperature, solar irradiation, and effective sky temperature are \(-40^{\circ} \mathrm{C}, 1100 \mathrm{~W} / \mathrm{m}^{2}\), and \(235 \mathrm{~K}\), respectively. What is the temperature of the wing's top surface? The properties of the air may be approximated as \(\rho=0.470 \mathrm{~kg} / \mathrm{m}^{3}, \mu=1.50 \times\) \(10^{-5} \mathrm{~N} \cdot \mathrm{s} / \mathrm{m}^{2}, k=0.021 \mathrm{~W} / \mathrm{m} \cdot \mathrm{K}\), and \(P r=0.72\).

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