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Balsa to the Wall Aerodynamics PDR: Airfoil Selection and Drag Analysis Study

Discover the meticulous design process of Team 2 as they choose airfoils, analyze drag buildup, and conduct flap analysis for a high-speed mission.

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Balsa to the Wall Aerodynamics PDR: Airfoil Selection and Drag Analysis Study

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  1. Aerodynamics PDR 2 Team 2: Balsa to the Wall Ashley Brawner Neelam Datta Xing Huang Jesse Jones Matt Negilski Mike Palumbo Chris Selby Tara Trafton

  2. Overview • Design Point • Airfoil Selection • Component Drag Buildup • Drag Polar • AR trade study • (CL)max Approximation • (Cl)max method • (CL)max Raymer method • Flap analysis

  3. The Design Point • Planform area based on approximated (CL)max and weight estimate • Dihedral angle of 0° taken from Roskam • Design speed decreased from 150 ft/sec • Designed to high speed mission

  4. Airfoil Selection: Main Wing • Wing Section • NACA 1408 • Gives approximate 2D Cl needed for dash • Relatively thin for minimizing drag • Thick enough for structural strength

  5. Airfoil Selection: Tail • Tail Sections • Horizontal Stabilizer • Symmetric with low Cd over a wider range of a.o.a. compared to other similar airfoils • Symmetric Jones airfoil (≈8% t/c) • Vertical Stabilizer • NACA 0006

  6. Drag Build-up Method (Raymer) • Cfc = Component skin friction coefficient • FFc = Component form factor • Qc = Component interference effects • Swet,c = Component wetted area • Sref = Wing planform

  7. Component Coefficient of friction

  8. Inputs: Drag Build-up Method results

  9. Drag Polar

  10. AR Trade study

  11. AR Trade study

  12. (Cl)max Approximation • Compare XFOIL with Abbott & Doenhoff wind tunnel data • Conclusion • αClmax ≈ 0.8αClmax(XFOIL)

  13. Flap analysis • Use (CL)max approximation from Raymer • Ads • Use XFOIL to find (Cl)max with flaps • Observation - • Flapped (Cl)max follows linear trend • Determine maximum achievable (CL)max • Find flap configuration that acheives optimal (CL)max

  14. Flap analysis: (continued) • Use linear fit lines to find a Δ(Cl)max and then find Δ(CL)max with the following equation from Raymer: • ads • The ratio blank is based on the intial sizing of the wing area and tail span and is assumed to remain constant

  15. Flap Geometry: • flap hinge location (x/c) = 0.8 • maximum flap deflection = 35° • constant (cf/c) flap • (CL)max (w/ flaps) = 1.06 • (Cl)max (w/o flaps) = 0.85

  16. Summary Table

  17. Questions?

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