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Ashley Brawner Neelam Datta Xing Huang Jesse Jones

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Presentation on theme: "Ashley Brawner Neelam Datta Xing Huang Jesse Jones"— Presentation transcript:

1 Ashley Brawner Neelam Datta Xing Huang Jesse Jones
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 5.5 [lbs] Weight 0° Dihedral Angle 110 [ft/sec] Speed
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 Weight 5.5 [lbs] Dihedral Angle Speed 110 [ft/sec] Horizontal Tail Span 1.5 [ft]

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


6 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


8 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

9 Component Coefficient of friction

10 Drag Build-up Method results

11 Drag Polar

12 AR Trade study

13 AR Trade study

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





19 Flap analysis Ads Use (CL)max approximation from Raymer
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



22 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

23 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

24 Summary Table (CL)max (w/ flaps) 1.06 (CL)max (w/o flaps) 0.84 CD0
0.0253 AR 6 b 5 [ft] croot 16.24 [in] ctip 7.35 [in] troot 1.3 [in] ttip 0.6 [in] Flap location (x/c) 0.8 Maximum flap deflection 35°

25 Questions?

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