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a) Consider the wing of an aircraft as a flat plate of 25 m length in the flow directi (Figure 2). The plane is moving at 100 m/s in air that is at a pressure of 0.7 bar a a temperature of 10°C. The top surface of the wing absorbs solar radiation at a ra of 800 W/m2. Assume the wing to be of solid construction and to have a sing uniform temperature. Estimate the steady-state temperature of the wing. Refer Table A-15 for air thermophysical properties.

a) Consider the wing of an aircraft as a flat plate of 25 m length in the flow directi (Figure 2). The plane is moving at 100 m/s in air that is at a pressure of 0.7 bar a a temperature of 10°C. The top surface of the wing absorbs solar radiation at a ra of 800 W/m2. Assume the wing to be of solid construction and to have a sing uniform temperature. Estimate the steady-state temperature of the wing. Refer Table A-15 for air thermophysical properties.

Principles of Heat Transfer (Activate Learning with these NEW titles from Engineering!)
Principles of Heat Transfer (Activate Learning with these NEW titles from Engineering!)
8th Edition
ISBN:9781305387102
Author:Kreith, Frank; Manglik, Raj M.
Publisher:Kreith, Frank; Manglik, Raj M.
Chapter7: Forced Convection Inside Tubes And Ducts
Section: Chapter Questions
Problem 7.31P
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Q2 a) Consider the wing of an aircraft as a flat plate of 25 m length in the flow direction (Figure 2). The plane is moving at 100 m/s in air that is at a pressure of 0.7 bar and a temperature of 10°C. The top surface of the wing absorbs solar radiation at a rate of 800 W/m2. Assume the wing to be of solid construction and to have a single, uniform temperature. Estimate the steady-state temperature of the wing. Refer Table A-15 for air thermophysical properties. Air a conv 9's,abs = 800 W/m² Į U= 100 km/s Too=263 K p= 0.7 bar a conv tam Figure 2 - Ts L = 2.5m
Transcribed Image Text:Q2 a) Consider the wing of an aircraft as a flat plate of 25 m length in the flow direction (Figure 2). The plane is moving at 100 m/s in air that is at a pressure of 0.7 bar and a temperature of 10°C. The top surface of the wing absorbs solar radiation at a rate of 800 W/m2. Assume the wing to be of solid construction and to have a single, uniform temperature. Estimate the steady-state temperature of the wing. Refer Table A-15 for air thermophysical properties. Air a conv 9's,abs = 800 W/m² Į U= 100 km/s Too=263 K p= 0.7 bar a conv tam Figure 2 - Ts L = 2.5m
TABLE A-15 Properties of air at 1 atm pressure Dynamic Kinematic Prandtl Temp., Density, Specific Heat, Cp. J/kg. °C Thermal Conductivity, k, W/m. °C Thermal Diffusivity, a, m²/s Viscosity, Number, T, °C p. kg/m³ Viscosity, v, m²/s μ, kg/m-s Pr -150 2.866 983 -100 2.038 3.013 x 10-6 5.837 x 10-6 966 0.01171 0.01582 0.01979 0.02057 0.7246 0.7263 0.7440 -50 1.582 -40 1.514 999 9.319 x 10-6 1002 1.008 x 10-5 0.7436 1004 0.02134 -30 1.451 -20 1.394 -10 8.636 x 10-6 1.189 x 10-6 1.474 x 10-5 1.527 x 10-5 1.579 x 10-5 1.630 x 10-5 1.680 x 10-5 1.729 x 10-5 1.754 x 10-5 1.778 x 10-5 1005 0.02211 1.341 1006 0.02288 1.087 x 10-5 1.169 x 10-5 1.252 x 10-5 1.338 x 10-5 1.382 x 10-5 0.7425 0.7408 0.7387 0.7362 1006 0.02364 1006 0.02401 1006 0.02439 1.426 x 10-5 1.470 x 10-5 0.02476 0 1.292 5 1.269 10 1.246 15 1.225 20 1.204 25 1.184 30 1.164 35 1.145 40 1.127 1.802 x 10-5 0.7350 0.7336 0.7323 0.7309 1007 1007 0.02514 1.516 x 10-5 1.825 x 10-5 1.849 x 10-5 1.562 x 10-5 0.02551 0.02588 1.872 x 10-5 1007 1007 1007 1007 0.7296 0.7282 0.7268 0.7255 0.02625 0.02662 0.02699 1.608 x 10-5 1.655 x 10-5 1.702 x 10-5 1.750 x 10-5 1.895 x 10-5 1.918 x 10-5 1.941 x 10-5 45 1.109 1007 50 1.092 1007 0.02735 1.963 x 10-5 1.798 x 10-5 1.896 x 10-5 1.059 1007 60 70 1.028 0.02808 0.7241 0.7228 0.7202 0.7177 2.008 x 10-5 2.052 x 10-5 1007 0.02881 1.995 x 10-5 4.158 x 10-6 8.036 x 10-6 1.252 x 10-5 1.356 x 10-5 1.465 x 10-5 1.578 x 10-5 1.696 x 10-5 1.818 x 10-5 1.880 x 10-5 1.944 x 10-5 2.009 x 10-5 2.074 x 10-5 2.141 x 10-5 2.208 x 10-5 2.277 x 10-5 2.346 x 10-5 2.416 x 10-5 2.487 x 10-5 2.632 x 10-5 2.780 x 10-5 2.931 x 10-5 3.086 x 10-5 3.243 x 10-5 3.565 x 10-5 3.898 x 10-5 4.241 x 10-5 4.593 x 10-5 4.954 x 10-5 5.890 x 10-5 6.871 x 10-5 7.892 x 10-5 8.951 x 10-5 1.004 x 10-4 1.117 x 10-4 1.352 x 10-4 1.598 x 10-4 1.855 x 10-4 2.122 x 10-4 2.398 x 10-4 3.908 x 10-4 80 0.9994 1008 0.02953 2.096 x 10-5 2.097 x 10-5 0.7154 90 0.9718 1008 2.139 x 10-5 2.201 x 10-5 1009 2.181 x 10-5 2.306 x 10-5 0.03024 0.03095 0.03235 0.03374 0.7132 0.7111 100 0.9458 120 0.8977 140 0.8542 2.264 x 10-5 2.522 x 10-5 1011 1013 0.7073 2.345 x 10-5 2.745 x 10-5 0.7041 1016 2.420 x 10-5 2.975 x 10-5 0.03511 0.03646 0.7014 1019 2.504 x 10-5 3.212 x 10-5 0.6992 160 0.8148 180 0.7788 200 0.7459 250 0.6746 300 0.6158 0.03779 3.455 x 10-5 0.6974 1023 1033 0.04104 0.04418 1044 4.091 x 10-5 4.765 x 10-5 0.6946 0.6935 350 0.5664 2.577 x 10-5 2.760 x 10-5 2.934 x 10-5 3.101 x 10-5 3.261 x 10-5 3.415 x 10-5 1056 0.04721 5.475 x 10-5 400 0.5243 1069 0.6937 0.6948 0.05015 6.219 x 10-5 0.4880 1081 0.05298 450 500 0.4565 6.997 x 10-5 0.6965 1093 0.05572 3.563 x 10-5 7.806 x 10-5 0.6986 600 0.4042 1115 0.06093 3.846 x 10-5 9.515 x 10-5 0.7037 700 0.3627 1135 0.06581 4.111 x 10-5 1.133 x 10-4 0.7092 800 0.3289 1153 0.07037 4.362 x 10-5 1.326 x 10-4 0.7149 0.3008 1169 4.600 x 10-5 1.529 x 10-4 900 1000 0.2772 0.07465 0.07868 0.7206 1184 4.826 x 10-5 1.741 x 10-4 0.7260 1500 0.1990 1234 5.817 x 10-5 2.922 x 10-4 0.09599 0.11113 0.7478 2000 0.1553 1264 5.664 x 10-4 6.630 x 10-5 4.270 x 10-4 0.7539 pressure P (in atm) other than 1 atm are Note: For ideal gases, the properties C, K., and Pr are independent of pressure. The properties p, v, and a at a determined by multiplying the values of p at the given temperature by P and by dividing vand a by P. Source: Data generated from the EES software developed by S. A. Klein and F. L. Alvarado. Original sources: Keenan, Chao, Keyes, Gas Tables, Wiley, 198; and Thermophysical Properties of Matter, Vol. 3: Thermal Conductivity, Y. S. Touloukian, P. E. Liley, S. C. Saxena, Vol. 11: Viscosity, Y. S. Touloukian, S.C. Saxena, and P. Hestermans, IFI/Plenun, NY, 1970, ISBN 0-306067020-8.
Transcribed Image Text:TABLE A-15 Properties of air at 1 atm pressure Dynamic Kinematic Prandtl Temp., Density, Specific Heat, Cp. J/kg. °C Thermal Conductivity, k, W/m. °C Thermal Diffusivity, a, m²/s Viscosity, Number, T, °C p. kg/m³ Viscosity, v, m²/s μ, kg/m-s Pr -150 2.866 983 -100 2.038 3.013 x 10-6 5.837 x 10-6 966 0.01171 0.01582 0.01979 0.02057 0.7246 0.7263 0.7440 -50 1.582 -40 1.514 999 9.319 x 10-6 1002 1.008 x 10-5 0.7436 1004 0.02134 -30 1.451 -20 1.394 -10 8.636 x 10-6 1.189 x 10-6 1.474 x 10-5 1.527 x 10-5 1.579 x 10-5 1.630 x 10-5 1.680 x 10-5 1.729 x 10-5 1.754 x 10-5 1.778 x 10-5 1005 0.02211 1.341 1006 0.02288 1.087 x 10-5 1.169 x 10-5 1.252 x 10-5 1.338 x 10-5 1.382 x 10-5 0.7425 0.7408 0.7387 0.7362 1006 0.02364 1006 0.02401 1006 0.02439 1.426 x 10-5 1.470 x 10-5 0.02476 0 1.292 5 1.269 10 1.246 15 1.225 20 1.204 25 1.184 30 1.164 35 1.145 40 1.127 1.802 x 10-5 0.7350 0.7336 0.7323 0.7309 1007 1007 0.02514 1.516 x 10-5 1.825 x 10-5 1.849 x 10-5 1.562 x 10-5 0.02551 0.02588 1.872 x 10-5 1007 1007 1007 1007 0.7296 0.7282 0.7268 0.7255 0.02625 0.02662 0.02699 1.608 x 10-5 1.655 x 10-5 1.702 x 10-5 1.750 x 10-5 1.895 x 10-5 1.918 x 10-5 1.941 x 10-5 45 1.109 1007 50 1.092 1007 0.02735 1.963 x 10-5 1.798 x 10-5 1.896 x 10-5 1.059 1007 60 70 1.028 0.02808 0.7241 0.7228 0.7202 0.7177 2.008 x 10-5 2.052 x 10-5 1007 0.02881 1.995 x 10-5 4.158 x 10-6 8.036 x 10-6 1.252 x 10-5 1.356 x 10-5 1.465 x 10-5 1.578 x 10-5 1.696 x 10-5 1.818 x 10-5 1.880 x 10-5 1.944 x 10-5 2.009 x 10-5 2.074 x 10-5 2.141 x 10-5 2.208 x 10-5 2.277 x 10-5 2.346 x 10-5 2.416 x 10-5 2.487 x 10-5 2.632 x 10-5 2.780 x 10-5 2.931 x 10-5 3.086 x 10-5 3.243 x 10-5 3.565 x 10-5 3.898 x 10-5 4.241 x 10-5 4.593 x 10-5 4.954 x 10-5 5.890 x 10-5 6.871 x 10-5 7.892 x 10-5 8.951 x 10-5 1.004 x 10-4 1.117 x 10-4 1.352 x 10-4 1.598 x 10-4 1.855 x 10-4 2.122 x 10-4 2.398 x 10-4 3.908 x 10-4 80 0.9994 1008 0.02953 2.096 x 10-5 2.097 x 10-5 0.7154 90 0.9718 1008 2.139 x 10-5 2.201 x 10-5 1009 2.181 x 10-5 2.306 x 10-5 0.03024 0.03095 0.03235 0.03374 0.7132 0.7111 100 0.9458 120 0.8977 140 0.8542 2.264 x 10-5 2.522 x 10-5 1011 1013 0.7073 2.345 x 10-5 2.745 x 10-5 0.7041 1016 2.420 x 10-5 2.975 x 10-5 0.03511 0.03646 0.7014 1019 2.504 x 10-5 3.212 x 10-5 0.6992 160 0.8148 180 0.7788 200 0.7459 250 0.6746 300 0.6158 0.03779 3.455 x 10-5 0.6974 1023 1033 0.04104 0.04418 1044 4.091 x 10-5 4.765 x 10-5 0.6946 0.6935 350 0.5664 2.577 x 10-5 2.760 x 10-5 2.934 x 10-5 3.101 x 10-5 3.261 x 10-5 3.415 x 10-5 1056 0.04721 5.475 x 10-5 400 0.5243 1069 0.6937 0.6948 0.05015 6.219 x 10-5 0.4880 1081 0.05298 450 500 0.4565 6.997 x 10-5 0.6965 1093 0.05572 3.563 x 10-5 7.806 x 10-5 0.6986 600 0.4042 1115 0.06093 3.846 x 10-5 9.515 x 10-5 0.7037 700 0.3627 1135 0.06581 4.111 x 10-5 1.133 x 10-4 0.7092 800 0.3289 1153 0.07037 4.362 x 10-5 1.326 x 10-4 0.7149 0.3008 1169 4.600 x 10-5 1.529 x 10-4 900 1000 0.2772 0.07465 0.07868 0.7206 1184 4.826 x 10-5 1.741 x 10-4 0.7260 1500 0.1990 1234 5.817 x 10-5 2.922 x 10-4 0.09599 0.11113 0.7478 2000 0.1553 1264 5.664 x 10-4 6.630 x 10-5 4.270 x 10-4 0.7539 pressure P (in atm) other than 1 atm are Note: For ideal gases, the properties C, K., and Pr are independent of pressure. The properties p, v, and a at a determined by multiplying the values of p at the given temperature by P and by dividing vand a by P. Source: Data generated from the EES software developed by S. A. Klein and F. L. Alvarado. Original sources: Keenan, Chao, Keyes, Gas Tables, Wiley, 198; and Thermophysical Properties of Matter, Vol. 3: Thermal Conductivity, Y. S. Touloukian, P. E. Liley, S. C. Saxena, Vol. 11: Viscosity, Y. S. Touloukian, S.C. Saxena, and P. Hestermans, IFI/Plenun, NY, 1970, ISBN 0-306067020-8.
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