use registration number 29. Use Catia software to do this. and please generate a google drive and upload the file in that google drive and paste here the link of that Google drive. thank you

Create a wing by importing airfoil NACA 23012. N is the number of last two digits of registration number of respective student. Root Chord should be 0.5*N, Tip Chord should be 0.75*Root Chord, Sweep of 0.25*N and a geometric wing twist of 0.1*N degrees. Half span of the wing should be 5*Root chord. Fuselage should have a maximum cross sectional diameter equal to 0.75*Root chord of the wing. Try to give fuselage an aerodynamic shape. Distance from quarter chord of wing to nose of fuselage should be 1/3rd of total length of fuselage. Length of fuselage should be equal to 0.8*Span. Tail area should be equal to 0.35*Area of the wing. Sweep of the tail should be between 30-45 degrees (you can chooe any sweep angle between given range). Tail Root chord should be 0.6* root chord of wing. Tip chord should be 0.3*root chord of tail. Half span should be equal to maximum diameter of the fuselage. For Tail use NACA 0012 Airfoil. Create every part separately and than assemble them togather using assembly design