Team “Canard” September 19th, 2006 Aerodynamics 1 QDR Team “Canard” September 19th, 2006

Overview Aircraft Geometry: Aerodynamic Mathematical Model: Summary - Airfoil selection for wing and tail - Wing and tail configuration - Aspect ratio and wetted area - 3-View drawing Aerodynamic Mathematical Model: - CL - CD - CLMax Summary AAE 451 Team 1

Preliminary Airfoil Selection Wing Airfoil: - Looked at pylon racers - MH 43 common airfoil - Low Reynolds number airfoil Tail Airfoil: - NACA 0009 common in tail surfaces - Thin, lower induced and parasite drag MH 43 NACA 0009 AAE 451 Team 1

Wing Geometry METHOD Fixed thanks to historical data: Aspect ratio = 10 Taper ratio = 0.45 To be determined: Sweep angle Dihedral angle Wing span AAE 451 Team 1

Wing Geometry Top View s a b Wing span = 6.45 ft C a b s Swing = 4.16 ft2 Wing span = 6.45 ft Too much for structure Wing span = 6 ft Aspect ratio = 8.65 Sweep angle = = 9.3 degrees AAE 451 Team 1

Same airfoil all along the wing Wing Geometry Front View d troot ttip Chordtip = 0.4 Chordroot ttip = 0.4 troot Same airfoil all along the wing From the airfoil section, we know : troot = 0.0846 Chordroot troot = 0.0753 ft ttip = 0.0846 Chordtip ttip = 0.0338 ft Dihedral angle = = 0.73 degrees AAE 451 Team 1

Tail Geometry Top View Horizontal tail : Vertical tail : 11.4 deg Taper ratio : 0.6 Aspect ratio : 10 Sweep angle : 11.4 deg No dihedral 0.47 ft Shtail = 0.36 ft2 0.28 ft 1.88 ft Swing = 4.16 ft2 AAC = 0.65 ft D = 2.25 ft with Vertical tail : 0.7 ft 0.65 ft Degrees of freedom on the size for control and stability AAE 451 Team 1

Wing and Tail Geometry Wing Horizontal Tail Span 6 ft 1.88 ft Sweep Angle 9.3° 11.4° Taper Ratio 0.45 0.6 Dihedral Angle 0.73° 0° AAE 451 Team 1

Aircraft Wetted Area (Historical data) AAE 451 Team 1

Aircraft Wetted Area Fuselage wetted area estimate : Wing/tail wetted area estimate : Fuselage : Swet-fuselage = 2.88 ft2 Wing : Sexposed-wing = 3.92 ft2 Swet-wing = 7.92 ft2 Horizontal tail : Sexposed-htail = 0.33 ft2 Swet-htail = 0.67 ft2 Vertical tail : Sexposed-vtail = 0.196 ft2 Swet-vtail = 0.39 ft2 AAE 451 Team 1

3-View Drawing AAE 451 Team 1

Mathematical Model CL: - CD: CLMax: - CL at αstall AAE 451 Team 1

Mathematical Model 2D Estimation from XFOIL 2D Coefficients Clo = 0.151 Clα = 0.104/° Clmax = 1.082 AAE 451 Team 1

Mathematical Model 2D Estimation Cont… 2D Drag Coefficients Cdo = 0.00589 AAE 451 Team 1

2D to 3D Calculations Find CL from lifting line : Find e : Find k : Find CD for 3D : Find CDo : AAE 451 Team 1

2D/3D Comparison 2D plotted in blue 3D plotted in red AAE 451 Team 1

Summery Aircraft Geometry: Aerodynamic Mathematical Model: - Airfoil selection for wing and tail - Wing and tail configuration - Aspect ratio and wetted area - 3-View drawing Aerodynamic Mathematical Model: - CL - CD - CLMax AAE 451 Team 1

Questions Any Questions? AAE 451 Team 1