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Team 5 Aerodynamics QDR #2

Team 5 Aerodynamics QDR #2. Scott Bird Mike Downes Kelby Haase Grant Hile Cyrus Sigari Sarah Umberger Jen Watson. Presentation Outline. Updated Airfoil Lift Coefficient Pitching Moment. Airfoil Re-Selection . 24 inch chord. NACA 2412 Selig 1223.

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Team 5 Aerodynamics QDR #2

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  1. Team 5 Aerodynamics QDR #2 • Scott Bird • Mike Downes • Kelby Haase • Grant Hile • Cyrus Sigari • Sarah Umberger • Jen Watson QDR

  2. Presentation Outline • Updated Airfoil • Lift Coefficient • Pitching Moment QDR

  3. Airfoil Re-Selection 24 inch chord NACA 2412 Selig 1223 QDR

  4. Method Used to Calculate Lift Coefficient • Ran XFOIL for NACA 2412 to get 2-D Data • Converted to 3-D • Ran XFOIL again for NACA 0012 horizontal tail • Converted to 3-D • Used method described in Roskam Part VI, CH8 QDR

  5. Lift Coefficient • CL= CLo + CLα* α + CLδe *δe • CL= 0.1764 + 0.1386* α + 0.0336*δe • (note α and δe in degrees) QDR

  6. Effects of Elevator Deflection on Lift Coefficient QDR

  7. Method used for calculating Pitching Moment Coeff. Utilized Lift Coefficient data and calculations described earlier in accordance with method described in Roskam, Chapter 3 of AAE 421 Book. QDR

  8. Pitching Moment Coefficient about Quarter Chord • Cm= Cmo + Cmα* α + Cmδe *δe • Cm= - 0.0280 - 0.1562* α- 0.0898*δe • (note α and δe in degrees) QDR

  9. Pitching Moment • “Believability” Check • Cm0 Range +.15 to - .15 • Cmα Range +1 to -4 [deg-1] • Cmδe Range 0 to -4 [deg-1] • (note: not necessarily correct, just in a “believable” range of typical values) • (Roskam p.87,88 Airplane Flight Dynamics and Automatic Flight Controls) QDR

  10. Pitching Moment Coefficient QDR

  11. Questions? Questions? QDR

  12. Calculations • Re = 432,0000; M = 0.029 (Takeoff Conditions) 2-D to 3-D Conversion • CLα = Cl α/(1 + (57.3*Cl α/(π*e*A))) [deg-1] • [57.3 deg/rad conversion](from AAE 251 book) • CL = Cl*(CLα/Cl α) • [calculated for CL0 using Cl0] (Hepperle) QDR

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