initial commit / add all books

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+clc;

+T1=290; // Temperature at inlet in kelvin

+n=10; // Number of stages

+rp=6.5; // Pressure ratio

+m=3; // mass flow rate in kg/s

+eff_C=0.9; // isentropic efficiency of the compression

+ca=110; // Axial velocity in m/s

+u=180; // Mean blade velocity in m/s

+Cp=1.005; // Specific heat in kJ/kg K

+r=1.4; // Specific heat ratio

+R=287; // Characteristic gas constant in J/kg K

+

+T_2=(rp)^((r-1)/r)*T1; // temperature after isentropic compression

+T2=((T_2-T1)/eff_C)+T1; // Temperature after actual compression

+P=m*Cp*(T2-T1); // Power given to the air

+Del_Tstage=(T2-T1)/n; // Temperature rise per stage

+Del_ct=Cp*10^3*Del_Tstage/u; // For work done per kg of air per second

+// To find blade angles let solve the following equations

+// Del_ct=ca(tan beta_1-tan beta_2) for symmetrical stages

+// u=ca(tan beta_1=tan beta_2) for degree of reaction = 0.5

+// Solving by matrix method

+A=[1,-1;1,1]; C=[Del_ct/ca;u/ca];

+B=A\C;

+// Blade angles at entry and exit

+beta_1=atand(B(1));

+beta_2=atand(B(2));

+

+disp ("kW   (roundoff error)",P,"Power given to the air = ");

+disp ("degree",beta_2,"Blade angle at exit = ","degree",beta_1,"Blade angle at inlet = ");