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diff --git a/3685/CH14/EX14.12/Ex14_12.sce b/3685/CH14/EX14.12/Ex14_12.sce
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+clear
+clc
+// Given that
+L = 60 // Cooling load in kW
+p = 1 // Pressure in bar
+t = 20 // Temperature in degree celsius
+v = 900 // Speed of aircraft in km/h
+p1 = 0.35 // Pressure in bar
+T1 = 255 // Temperature in K
+nd = .85 // Diffuser efficiency 
+rp = 6 // Pressure ratio of compressor
+nc = .85 // Copressor efficiency 
+E = 0.9 // Effectiveness of air cooler
+nt = 0.88 // Turbine efficiency 
+p_ = 0.08 // Pressure drop in air cooler in bar
+p5 =  1.08 // Pressure in bar
+cp = 1.005 // Heat capacity of air at constant pressure in kJ/kgK
+gama = 1.4 // Ratio of heat capacities of air
+printf("\n Example 14.12\n")
+V = v*(5/18)
+T2_ = T1 + (V^2)/(2*cp*1000)
+T2 = T2_
+p2_ = p1*((T2_/T1)^((gama/(gama-1))))
+p2 = p1 + nd*(p2_-p1)
+p3 = rp*p2
+T3_ = T2*((p3/p2)^((gama-1)/gama))
+T3 = T2 + (T3_-T2)/nc
+P = cp*(T3-T2)
+p4 = p3 - p_
+T4 = T3 - E*(T3-T2)
+T5_ = T4/((p4/p5)^(.286))
+T5 = T4 - (T4-T5_)/nt
+RE = cp*(t+273 - T5)
+m = L/51.5
+Pr = m*P
+COP = L/Pr
+printf("\n Mass flow rate of air flowing through the cooling system is %f kg/s",m)
+printf("\n COP is %f ",COP)
+//The answers vary due to round off error