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

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

3. Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 3  Wing Geometry  Zero Sweep  Zero Dihedral  Taper Ratio = 0.45  Aspect Ratio = 11.25  Wing Span = 75 inch  Wing Area = 500 sq. inch Working on Improving Aspect Ratio Selection

4. Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 4  Induced Drag Decreases with Aspect Ratio  increases span efficiency  reduces K 1 Induced Drag for C L at high speed

5. Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 5  Aspect Ratio Desired to be as high as possible  Predicted Aspect Ratio Constraints:  Structure Strength i) Bending Moment ii) Wing Twist  Manufacturing (CNC) machine size Currently working with Structure Group to determine best Aspect Ratio

6. 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

7. Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 7 Total Wetted Area = 12.15 sq.ft  Nose : Surface area of a semi- sphere: Anose=2*π*r²  Fuselage Approx [excluding nose] Lateral area of a cone: Afuse= (π * R) * [sqrt(R² + H²)]  Main Wing: Aw=2*SW  Horizontal Tail: Ah=2*SHT  Vertical Tail: Av=2*SVT

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

9. Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 9  NASG Database [UiUC Windtunnel Data]  Main Constraint [if not it will crash at V=30ft/s]: CLmax = 1.4 Vstall= 30ft/s Re Number ≈110,000  Optimized for: Minimum C d0 at high speed V speed =130 ft/s Re Number ≈ 500,000 http://www.nasg.com/afdb/list-polar-e.phtml

10. Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 10  Coefficient of Lift to maintain Steady Level Flight : Required CL max_with_flap = 1.4 Re Number= 110,000 Cl max 2-D without flap ≈ 1.3 [estimated using various airfoil] Cl max 2-D  CL max 3-D  Cl max 3-D with Flap Cl max DecreasesCl max Increases

11. Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 11 Pick airfoil with Clmax ≈ 1.3 Repeat for all available Airfoil

12. Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 12 Optimize for minimum drag at high-speed flight:  V speed = 130 ft/s  Re ≈ 500,000 (not available in database)  Used Re ≈ 300,000 [wind tunnel data]  XFOIL for Re = 500,000 on 3 final selected airfoil [Check if wind tunnel trend hold]

13. Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 13 Optimize Cd0 Minimize Cl at α 0 reduce induced drag Optimize Clmax

14. Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 14  Best Three Airfoils:  Selig / Donovan SD7032  Selig S4083  SG 6042 Selected Airfoil

15. Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 15 SD 7032 : Cd 0 =0.0058 MH 45 : Cd 0 =0.0056 MH 32 : Cd 0 =0.0050

16. Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 16  Horizontal Tail NACA 0009  Minimize Drag  small rudder deflection to account for motor & propeller torque  Vertical Tail NACA 0009  Minimize Drag  Elevator deflection will produce enough pitch down and pitch up moment for all mission required flight condition

17. Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 17  2-D Experimental Data (NASG Database)  Stall Constraint (Re=100,000)

18. Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 18  Convert 2-D to 3-D (Brandt pg. 145)  Span Efficiency Factor (e)

19. Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 19 2-D XFOIL Analysis –Flap Deflection: 35 [deg]

20. Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 20 Convert to 3-D (Raymer pg. 326) flapped area over wing area angle of hinge line to center line

21. Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 21  Added Effect of Flaps (Raymer pg. 326)

22. Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 22 Downward Force Required for Stability Downwash from wing reduces AoA seen by tail (Brandt pg. 154-155) tail area over wing area downwash empirical curve fit 3-D lift curve slope of tail taper ratio

23. Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 23  Compute Skin Friction Drag  Oswald Efficiency Factor (e)

24. Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 24  Stall Speed

25. Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 25  Cruise Speed

26. Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 26  Lift Coefficient of Whole Aircraft

27. Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 27  Moment Coefficient of Whole Aircraft

28. Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 28

29. Click to edit Master title style Click to edit Master text styles Second level Third level Fourth level Fifth level 29 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