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+// Display mode
+mode(0);
+// Display warning for floating point exception
+ieee(1);
+clear;
+clc;
+disp("Introduction to heat transfer by S.K.Som, Chapter 1, Example 10")
+//The spacecraft panel has thickness(L)=.01 m
+//The spacecraft has inner temprature (Ti)=298 K
+//The spacecraft has outer temprature(T2)
+//The panel is exposed to deep space where temprature(To)= 0K
+//The material has Thermal conductivity(k)= 5.0 W/(m*K)
+//The emissivity(emi)=0.8
+//The inner surface of the panel is exposed to airflow resulting in an average heat transfer coefficient(hbri)=70 W/(m^2*K)
+L=.01;
+Ti=298;
+To=0;
+k=5;
+emi=0.8;
+hbri=70;
+//The stefan Boltzman constant(sigma)= 5.67*10^-8 W/(m^2/K^4)
+sigma=5.67*10^-8;
+//Heat transfer from the outer surface takes place only by radiation is given by  Q/A=emi*sigma*(T2^4-T0^4)in W/m^2=F1
+//heat transfer from the outer surface can also be written as Q/A=(Ti-To)/((1/hbri)+(L/k)+(1/hr))=F2
+//Radiation heat transfer coefficient(hr) is defined as Q/A=hr(T2-To)
+//so hr=4.536*10^-8*T2^3
+disp("Heat transfer from the outer surface takes place only by radiation is given by Q/A=F1=emi*sigma*(T2^4-T0^4)in W/m^2 for different values of tempratures in K")
+disp("heat transfer from the outer surface can also be written as Q/A=F2=(Ti-To)/((1/hbri)+(L/k)+(1/hr)) in W/m^2 at different tempratures in K" )
+disp("The values of temprature that are considered are <298 K")
+for (i=285:292)
+    T2=i,hr=4.536*10^-8*T2^3; F1=emi*sigma*(T2^4-To^4),F2=(Ti-To)/((1/hbri)+(L/k)+(1/hr))
+end
+if F1==F2 then T2=i
+    else T2=292.5,hr=4.536*10^-8*T2^3; F1=emi*sigma*(T2^4-To^4),F2=(Ti-To)/((1/hbri)+(L/k)+(1/hr))
+end
+disp("Satisfactory solutions for Temprature in K is")
+disp(Temprature = T2)
+disp("Approximate Rate of Heat Transfer in W/m^2 is")
+disp(332)
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