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

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

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

2 2 Overview Design Point Airfoil Selection Component Drag Buildup Drag Polar AR trade study (C L ) max Approximation  (C l ) max method  (C L ) max Raymer method  Flap analysis

3 3 The Design Point Weight 5.5 [lbs] Dihedral Angle 0° Speed 110 [ft/sec] Horizontal Tail Span 1.5 [ft] Planform area based on approximated (C L ) max and weight estimate Dihedral angle of 0° taken from Roskam Design speed decreased from 150 ft/sec Designed to high speed mission

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

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6 6 Airfoil Selection: Tail Tail Sections  Horizontal Stabilizer Symmetric with low C d over a wider range of a.o.a. compared to other similar airfoils Symmetric Jones airfoil (≈8% t/c)  Vertical Stabilizer NACA 0006

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8 8 Drag Build-up Method (Raymer) C fc = Component skin friction coefficient FF c = Component form factor Q c = Component interference effects S wet,c = Component wetted area S ref = Wing planform

9 9 Component Coefficient of friction

10 10 Drag Build-up Method results Inputs:

11 11 Drag Polar

12 12 AR Trade study

13 13 AR Trade study

14 14 (C l ) max Approximation Compare XFOIL with Abbott & Doenhoff wind tunnel data Conclusion  α Clmax ≈ 0.8α Clmax(XFOIL)

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19 19 Flap analysis Use (C L ) max approximation from Raymer  Ads Use XFOIL to find (C l ) max with flaps Observation -  Flapped (C l ) max follows linear trend Determine maximum achievable (C L ) max Find flap configuration that acheives optimal (C L ) max

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22 22 Flap analysis: (continued) Use linear fit lines to find a Δ(C l ) max and then find Δ(C L ) 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

23 23 Flap Geometry: flap hinge location (x/c) = 0.8 maximum flap deflection = 35° constant (c f /c) flap (C L ) max (w/ flaps) = 1.06 (C l ) max (w/o flaps) = 0.85

24 24 Summary Table (C L ) max (w/ flaps)1.06 (C L ) max (w/o flaps)0.84 C D AR6 b5 [ft] c root [in] c tip 7.35 [in] t root 1.3 [in] t tip 0.6 [in] Flap location (x/c)0.8 Maximum flap deflection35°

25 25 Questions?


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