1. Patrick Dempsey Bridget Fitzpatrick Heather Garber Keith Hout Jong Soo Mok Aerodynamics Preliminary Design Review #1 October 3, 2000

2. Aircraft Geometry – 3-View

3. Aircraft Geometry -Airfoil section -Wing: Selig Donovan 7062 -Vertical tail: flat plate assumption -Horizontal tail: flat plate assumption -Airfoil selection process -Gather data on various airfoils -Run data thru xfoil -Compare xfoil to experimental data (www.nasg.com)

4. Aircraft Geometry

6. Airfoil Data – S/D 7062

8. Aircraft Geometry WingV-tailH-tail Span(ft)6.551.283.12 AvgChord(ft)1.501.001.06 Aspect Ratio2.201.303.00 Taper Ratio1.000.60 LE Sweep (deg)0.0021.018.43 Dihedral (deg)0.00 Planform Area (ft 2 ) 19.51.273.24

9. Aircraft Geometry -Aircraft wetted area: 59.5 ft 2 -Wing – 38.70 ft 2 -Struts -.83 ft 2 -Tails – 9.01 ft 2 -Landing gear -.003 ft 2 Aspect ratio of wing: 2.2

10. Aerodynamic Mathematical Model -Lift Coefficient - -Drag Coefficient - -Clmax - 2D: 1.53 - 3D: 1.22 CDo=Cdwing+Cdfuselage+Cdvtail+Cdhtail+CdLg+CdStrut CD=CDo+CDi CDi=(CL^2)/(pi*AR*e) CL=Clalpha*(alpha-alpha0lift)

11. Questions?