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+clc; funcprot(0);
+//Example 10.6 Induced drag of tappered wings
+
+// Initialisation of variables
+b = 46;
+w = 4;
+c = 8;
+r = 2;
+//data from figure 10.9
+CO = sqrt(6^2+19^2);
+CH = sqrt(19.93^2 - 2^2);
+EOH = atand(6/19);
+COH = acosd(2/19.93);
+GOH = 270 - EOH - COH;
+Area_ABCD = 2*c;
+Area_BGOC = 19*(2+8)*0.5;
+Area_COH = 0.5*r*CH;
+Area_GOH = GOH/360*(%pi*r^2);
+
+// Calculations
+Area_half_wing = Area_ABCD + Area_BGOC + Area_COH + Area_GOH;
+S = 2*Area_half_wing;
+AR = b^2/S;
+
+//Results 
+disp(AR,"Required aspect ratio :" );