Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 1

Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 2  Aircraft Geometry  Airfoil Selection [wing, vertical tail and horizontal tail]  Wing and Tail Geometry  3 – view Drawing  Aerodynamic Modeling  Method  Coefficient of Lift and Drag

Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 3  Wing NACA 4410  C Lmax and C D fits mission requirement  Horizontal Tail NACA 0009  Minimize Drag  Vertical Tail NACA 0009  Minimize Drag  Small deflection compensate Propeller torque

Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 4  Wing Geometry  Zero Sweep  Zero Dihedral  Taper Ratio = 0.4  Aspect Ratio =  Wing Span = 75 inch  Wing Area ≈ 500 sq. inch

Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 5 Volume Coefficient Horizontal Tail Moment Arm Horizontal Tail Area Horizontal Tail Area Wing Mean Wing Chord Volume Coefficient Vertical Tail Moment Arm Vertical Tail Area Vertical Tail Area Wing Wing Span

Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 6  Horizontal Tail Geometry  Span = 20 inch  Root Chord = 7 inch  Tip Chord = 4.8 inch  Area ≈ 108 sq. inch  Vertical Tail Geometry  Root Chord = 8 inch  Tip Chord = 4 inch  Area ≈ 53 sq. inch

Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 7 Fuselage Approximation Lateral area of a cone: (π * R) * [sqrt(R² + H²)] Surface area of a sphere: 4*π*r² Main Wing: 2*S W Horizontal Tail: 2*S HT Vertical Tail: 2*S VT A/C Wetted Area: 1750 sq. in

Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 8

Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 9  XFOIL  Compute 2-D Data  Find approximate stall angle  Derive Cla – slope of lift curve  Convert to 3-D e = span efficiency factor Cla – 2-D Cl-alpha slope

Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 10  Compute Effect of Flap (Brandt pg ) Ratio of flapped area to total wing area Sweep angle of flap hinge 2-D change in alpha max

Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 11  Compute Effect of Tail (Brandt pg ) St/S - tail area over wing area De/da - empirical curve fit CLat – 3-D CL-alpha slope of tail

Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 12  Compute Total Lift Coefficient  Compute Total Drag Coefficient CDo = k1 = e = 0.72

Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 13  Wing at Take-Off (Main Wing, Flaps, Tail)  Re: ~100,000  Max alpha: ~ [deg]

Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 14  Wing at Cruise Conditions (Main Wing, Tail)  Re: ~600,000

Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 15  Drag Polar  Take-Off Speed  Cruise Speed Stall Cruise

Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 16  More Accurately Define C Lmax  Possibly re-design tail so that C D is lower at cruise conditions

Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 17