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+clc; funcprot(0);
+//Example 11.3 Lift at subsonic speed
+
+// Initialisation of variables
+alp_z = -4;                 //Angle of attack at zero lift
+M16 = 0.16;
+Cl = 0.3;
+alp = 1.5;
+M0 = 0;
+M65 = 0.65;
+alp25 = 2.5;
+
+// Calculations
+//At M = 1.6
+DCl_by_Dalp16 = Cl/(alp-alp_z);
+
+//At M = 0
+DCl_by_Dalp0 = DCl_by_Dalp16*sqrt(1-M16^2);
+
+////At M = 0.65
+DCl_by_Dalp65 = DCl_by_Dalp0/sqrt(1-M65^2);
+
+Cl25 =  (alp25 - alp_z)*DCl_by_Dalp65;
+
+//Results 
+disp(Cl25,"Lift Coefficient at alpha = 2.5 degree: ") ;