The Barn Owls - PowerPoint PPT Presentation

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The Barn Owls

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  1. The Barn Owls Chris “Mo” Baughman Kate Brennan Christine Izuo Dan Masse Joe “Sal” Salerno Paul Slaboch Michelle Smith

  2. Design Drivers • High Rate of climb • Max. cruise speed

  3. Motivation • To build an aircraft which will take off (multiple times without crashing) • Accurately predict the performance of the designed aircraft • Maximize the speed and rate of climb

  4. Guidelines and Limitations • 400 – 800 sq. in. planform area • Given Astro-Cobalt 615G motor • Must be statically stable • Takeoff run < 300 ft. • No rockets!?!?!?!?!?!?!?!?!?!?!?!?!?!?!?

  5. Schedule and Deadlines • February 5th – Present Conceptual Design • February 26th – Present Detailed Design • March 4th – Complete Parts List • April 6th-9th – Ground Tests

  6. Weights

  7. Powerplant

  8. Thrust VS Speed

  9. Airfoil – GO 769

  10. Design Factors in Choosing Airfoil • Appropriate Reynolds Number Data (low speed) • Minimize Drag • t/c ~ 14% • wide drag bucket • Shallow increase in drag outside of drag bucket • Maximize Lift • High CL max

  11. Wing • Design Decisions • No sweep • Maximize lift • Ease of manufacture • Taper ratio of 0.25 • Minimize drag • Create large enough root chord length in order to provide clearance for payload • Slight dihedral for roll stability • Winglets enhance in-flight performance

  12. Fuselage • Airfoil-shaped fuselage serves as lifting surface • Also serves as a wing box which carries electronics • Conventional fuselage has been replaced by booms on order to minimize weight and drag

  13. Horizontal Tail • NACA 0009 Airfoil • Low drag, symmetric • Can Produce both Lift and Reverse Lift • Swept to maintain straight trailing edge to maximize control surface while minimizing planform area

  14. Take-off/Landing Estimations Take-off Distance = 176 ft. Landing Distance = 370 ft. (does not take into consideration climbing over an obstacle)

  15. Flaps • Slotted, 15% of total wing area • Used as flaperons • Enhanced lift for take-off • Control during flight • Speed brakes during landing

  16. Weight Distribution

  17. Static Stability Static Margin: 0.029753 (stable) CM,α= -0.78423 (stable) CN,β = 0.015653 (stable) CLβ = -0.015653 (stable)

  18. Conclusions