1 / 20

Team 5 Aerodynamics PDR

Team 5 Aerodynamics PDR. Presented By: Christian Naylor Eamonn Needler Charles Reyzer. Outline. Airfoil Sections Wing/Tail Geometry, Areas Mathematical Models Incidence Angles Control Surfaces Endurance. Airfoil Sections – Wing. Wing Eppler E212 Tail Eppler E169

wmarissa
Download Presentation

Team 5 Aerodynamics PDR

An Image/Link below is provided (as is) to download presentation Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author. Content is provided to you AS IS for your information and personal use only. Download presentation by click this link. While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server. During download, if you can't get a presentation, the file might be deleted by the publisher.

E N D

Presentation Transcript

  1. Team 5Aerodynamics PDR Presented By: Christian Naylor Eamonn Needler Charles Reyzer

  2. Outline • Airfoil Sections • Wing/Tail Geometry, Areas • Mathematical Models • Incidence Angles • Control Surfaces • Endurance AAE 451 – Team 5

  3. Airfoil Sections – Wing • Wing • Eppler E212 • Tail • Eppler E169 Horizontal Tail • NACA 0010 Vertical Tail AAE 451 – Team 5

  4. Geometry – Wing • Sizing • Weight : 0.6 lbs • W/S: 0.38 lbs/ft2 • Wing Area: 1.58 ft2 • Geometry Simplification • 2 Trapezoid Sections AAE 451 – Team 5

  5. Geometry – Wing • Defined Sweep Angles (Λ) • Defined taper ratio (λ) of 1st segment • Defined Span Ratio of 2 segments • Adjust to balance • Style • Aspect Ratio • Tip Chord feasibility AAE 451 – Team 5

  6. Geometry – Wing • Find Mean Aerodynamic Chord and Aerodynamic Center: AAE 451 – Team 5

  7. Geometry – Tail • Define Tail Volume Coefficients based on similar aircraft: • Cvt = 0.04 • Cht = 0.50 • Find tail areas • Svt=cvtbS/Lvt = 0.20 sq ft • Sht=chtcS/Lht = 0.47 sq ft AAE 451 – Team 5

  8. Geometry – Wing AAE 451 – Team 5

  9. Mathematical Model AAE 451 – Team 5

  10. Mathematical Model – Lift • Prandtl Lifting Line Theory1 • Elliptical Lift Distribution 1 Anderson, J.D., Fundamentals of Aerodynamics, New York, 2001, pp 351-416 AAE 451 – Team 5

  11. Mathematical Model – Lift Spanwise Γ Distribution Spanwise Downwash Distribution w(y) (m2/ft2s) Γ(y) (m2/s) Span (ft) Span (ft) AAE 451 – Team 5

  12. Mathematical Model – Lift Curve Spanwise Lift Coefficient Distribution Lift Coefficients vs. α CL and Cl CL Span (ft) α (deg) CLmax (Hembold): 0.74 Max Lift (Hembold): 1.10 lbf Max Lift at Cruise α: 0.74 lbf AAE 451 – Team 5

  13. Mathematical Model – Drag • Calculated from Lifting Line Theory1 • e=0.75 Drag Polar CD CL 1 Anderson, J.D., Fundamentals of Aerodynamics, New York, 2001, pp 351-416 AAE 451 – Team 5

  14. Mathematical Model – Moment Pitching Moment vs. α CM and Cm α (deg) 2 Raymer, D.P., Aircraft Design: A Conceptual Approach, Virginia, 1999, pp 315-378,493-494 AAE 451 – Team 5

  15. Mathematical Model – L/D • L/Dmax=11.89 • Cruise at α=3° L/D vs. α L/D α (deg) AAE 451 – Team 5

  16. Incidence Angles Spanwise Induced α αi Span (ft) AAE 451 – Team 5

  17. Control Surfaces • Ailerons • 50% to 90% on span • 15% to 25% of chord • Used junction to 95% chord and 25% of chord • Elevator • 0% - 90% on span • 25% to 50% of chord • Used 75% of span and 50% chord • Rudders • Same typical ranges as elevators • Used 10% to 90% on span and 50% chord AAE 451 – Team 5

  18. Control Surfaces • Sizes • Aileron Area: 0.082 ft2 (each) • Elevator Area: 0.176 ft2 • Rudder Area: 0.039 ft2 (each) AAE 451 – Team 5

  19. Endurance • Battery Wgt. Fraction = 0.064 • Battery Weight = 0.038 lbs. AAE 451 – Team 5

  20. Future Work • Revisit Sizing Code • Revisit Aerodynamic Center/ CG Calculations • Revisit Spanwise Lift Distribution • Look at Trade Studies AAE 451 – Team 5

More Related