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+

+

+// Display mode

+mode(0);

+

+// Display warning for floating point exception

+ieee(1);

+

+clc;

+disp("Principles of Heat Transfer, 7th Ed. Frank Kreith et. al Chapter - 7 Example # 7.1 ")

+

+//Diameter in m

+D = 0.3;

+//Cruising speed in m/s

+Uinfinity = 150;

+

+//At an altitude of 7500 m the standard atmospheric air pressure is 38.9 kPa and the density of the air is 0.566 kg/m3 (From Table 38 in Appendix 2).

+rho = 0.566;

+//Dynamic viscosity in kgm/s

+mu = 0.0000174;

+//Prandtl number

+Pr = 0.72;

+//Thermal conductivity in W/mK

+k = 0.024;

+

+//The heat transfer coefficient at the stagnation point (0) is, according to Eq. (7.2)

+

+disp("Heat transfer coefficient at stagnation point in W/m2K")

+//Heat transfer coefficient at stagnation point in W/m2K

+h = (((k*1.14)*((((rho*Uinfinity)*D)/mu)^0.5))*(Pr^0.4))/D

+

+disp("Distribution of the convection heat trans-fer coefficient over the forward portion of the wing")

+for o = 0:15:75 //o is the parameter used in the loop

+    //convection heat trans-fer coefficients in W/m2K

+  ho = h*(1-(o/90)^3);

+  // L.26: No simple equivalent, so mtlb_fprintf() is called.

+  mtlb_fprintf("At an angle of %5.2f degree, heat transfer coeffcient is %5.2f\n",o,ho)

+end;