initial commit / add all books

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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