reorganize file structure

archive/dragbuildup.m

@@ -0,0 +1,27 @@
+%ascorrea
+% FUCKA YOU EMPILICAR DATAR!!!
+
+fprintf('Fuselage Data');
+R_wf=input('\nInput Fuselage-wing Interference Factor (Fig 5.11):');
+C_fr=input('Input Flat Plate Friction Coeff. Fuselage(Fig 5.13)');
+fnratio=input('Input finesse ratio:');
+S_wetf=input('Input Fuselage Wetted Area:');
+fprintf('\nWing Data');
+R_ls=input('\nInput Lifting Surface Correction Factor:');
+C_fw=input('Input Flat Plate Friction Coeff. Wing(Fig 5.13)');
+L_prime=input('Input Airfoil Thickness Location Factor:');
+thickratio=input('Input Airfoil thickness (t/c):');
+S_wetw=input('Input Wing Wetted Area:');
+S_w=input('Input wing planform area:');
+answer=input('\n\nCompressible? Yes (1) or No (2)');
+if answer==1
+    M=input('Input Speed (Mach):');
+    c_fw=c_fw*(1-.09*M^2);
+end
+C_lw=input('Input lift Coeff.');
+
+
+C_dof=R_wf*C_fr*(1+(60/fnratio^3)+.0025*fnratio)*(S_wetf)/(S_w);
+C_dow=
+
+fprintf('Cdo: %f', Cd)