1 / 15

Aerodynamics PDR # 2 AAE451 – Team 3 November 18, 2003

Aerodynamics PDR # 2 AAE451 – Team 3 November 18, 2003. Brian Chesko Brian Hronchek Ted Light Doug Mousseau Brent Robbins Emil Tchilian. Aircraft Walk Around. Wing Span = 14.6 ft A/C Length = 10 ft. Conventional Tail – NACA 0012. Pusher. Internal Pod. Low wing – Clark Y.

jared
Download Presentation

Aerodynamics PDR # 2 AAE451 – Team 3 November 18, 2003

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. Aerodynamics PDR # 2 AAE451 – Team 3 November 18, 2003 Brian Chesko Brian Hronchek Ted Light Doug Mousseau Brent Robbins Emil Tchilian

  2. Aircraft Walk Around • Wing Span = 14.6 ft • A/C Length = 10 ft • Conventional Tail – NACA 0012 • Pusher Internal Pod • Low wing – Clark Y • Tricycle Gear

  3. Dimensions *Still some issues with sizing vertical tail

  4. Alpha L=0 Determination Xfoil runs of ClarkY foil at cruise and takeoff Cruise: αL=0= -3.5° Takeoff no flap: αL=0= -3.8° Takeoff 10° flap: αL=0= -7° Takeoff 15° flap: αL=0= -7.8°

  5. Stall Performance • CL needed = 1.19 • Wing without flaps reaches CL at a=13° • Wing stall possible • Wing with 15° flap deflection reaches CL at 11° Required CL Flaperons necessary to meet stall requirements

  6. NACA Empirical Data For ClarkY Foil Approximate Stall angle ~14° http://naca.larc.nasa.gov/reports/1933/naca-report-431/

  7. Stall Performance Required CL CD = 0.119 at required CL

  8. Cruise Performance CL needed = 0.366 CL achieved at a = 1.9° Total Lift produced = 57 lbf Total Drag = 2.6 lbf, L/D =21

  9. NACA Empirical Data For ClarkY Foil L/D at a = 2° is approximately 22 http://naca.larc.nasa.gov/reports/1933/naca-report-431/

  10. Operating Parameters

  11. Horizontal Tail Requires Tail Angle of -5° • AR = 3 • Span = 6 • Chord = 2 CL = -0.32 required of horizontal tail at cruise

  12. Fuselage Drag 0.67 ft 5 ft 1.33 ft • Assumptions • Cf for turbulent flow • Fuselage approximated as box • Interference factor, Q, 1.2 (low end of unfilleted low wings) • FF from Raymer Eq. (12.31)

  13. Drag Build Up at Cruise More to come…

  14. Summary Horizontal Tail • Foil: NACA 0012 • Taper Ratio = 1 • Dihedral Angle = 0º • AR = 3 • S = 12 ft2 • Angle of Incidence = -5° Wing • Foil: ClarkY • Taper Ratio = 1 • Dihedral Angle = 5° • AR = 5 • S = 42 ft2 • Angle of Incidence = 2°

  15. Questions?

More Related