team 5 aerodynamics qdr
DESCRIPTION
Team 5 Aerodynamics QDR. Presented By: Christian Naylor Charles Reyzer. Outline. Airfoil Sections Wing/Tail Geometry. Airfoil Sections - Overview. Selecting Wing Airfoils UIUC Airfoil Database Low Reynolds Airfoils (~200,000) Custom Jones airfoil (Joneplot) Selecting Tail Airfoils - PowerPoint PPT PresentationTRANSCRIPT
Team 5Aerodynamics QDR
Presented By: Christian Naylor Charles Reyzer
AAE 451 – Team 5February 8, 2005 2
Outline
Airfoil Sections Wing/Tail Geometry
AAE 451 – Team 5February 8, 2005 3
Airfoil Sections - Overview Selecting Wing Airfoils
UIUC Airfoil DatabaseLow Reynolds Airfoils (~200,000)Custom Jones airfoil (Joneplot)
Selecting Tail AirfoilsSymmetrical AirfoilsNACA Airfoils
AAE 451 – Team 5February 8, 2005 4
Airfoil Sections - Wing
Archer A18 F1C free flight airfoil
Eppler E169 Low Re airfoil
Eppler E193 Low Re airfoil
Eppler E212 Low Re airfoil
Custom RT Jones Airfoil (Joneplot)
0 0.2 0.4 0.6 0.8 1
-0.4
-0.3
-0.2
-0.1
0
0.1
0.2
0.3
0.4
0.5a18sm
0 0.2 0.4 0.6 0.8 1
-0.4
-0.3
-0.2
-0.1
0
0.1
0.2
0.3
0.4
e169
0 0.2 0.4 0.6 0.8 1
-0.4
-0.3
-0.2
-0.1
0
0.1
0.2
0.3
0.4
0.5e193
0 0.2 0.4 0.6 0.8 1
-0.4
-0.3
-0.2
-0.1
0
0.1
0.2
0.3
0.4
e212
0 0.2 0.4 0.6 0.8 1
-0.4
-0.3
-0.2
-0.1
0
0.1
0.2
0.3
0.4
0.5
Jone451
AAE 451 – Team 5February 8, 2005 5
Airfoil Sections - Wing
5 Airfoils Pre-Selected
Performance Comparisons
-5 0 5 10 15-1
-0.5
0
0.5
1
1.5
a18sme169e193e212Jone451
α (deg)
Clvs. α
Cl
AAE 451 – Team 5February 8, 2005 6
Airfoil Sections - Wing
-1 -0.5 0 0.5 1 1.50
0.01
0.02
0.03
0.04
0.05
0.06
0.07
0.08
0.09
0.1
a18sme169e193e212Jone451
Cl
Cd
Drag Polar
-5 0 5 10 15-0.14
-0.12
-0.1
-0.08
-0.06
-0.04
-0.02
0
0.02
0.04
a18sme169e193e212Jone451
Cm vs. α
Cd
α (deg)
Cm
AAE 451 – Team 5February 8, 2005 7
Airfoil Sections - Tail
NACA Airfoils selected
1 Wing Airfoil also run
α (deg)
Clvs. α
Cl
0 2 4 6 8 10 12 14 16 180
0.2
0.4
0.6
0.8
1
1.2
1.4
NACA 0010NACA 0012NACA 0014NACA 0016NACA 0018Eppler 169
AAE 451 – Team 5February 8, 2005 8
Airfoil Sections - Tail
Cl
Drag PolarCm vs. α
Cd
α (deg)
Cm
0 2 4 6 8 10 12 14 16 18-0.06
-0.04
-0.02
0
0.02
0.04
0.06
NACA 0010NACA 0012NACA 0014NACA 0016NACA 0018Eppler 169
0 0.2 0.4 0.6 0.8 1 1.2 1.40
0.02
0.04
0.06
0.08
0.1
0.12
0.14
0.16
0.18
0.2NACA 0010NACA 0012NACA 0014NACA 0016NACA 0018Eppler 169
AAE 451 – Team 5February 8, 2005 9
Airfoil Sections - Summary
Wing AirfoilEppler 193Eppler 212
Tail AirfoilNACA 0016Eppler 169
AAE 451 – Team 5February 8, 2005 10
Wing Geometry
From Sizing Weight: 1.752 lbs W/S:0.38 lb/ft2
Wing Area: 4.61 ft2
Sweep Angle 45°,15°,26°
Taper Ratio 1/3
AAE 451 – Team 5February 8, 2005 11
Wing Geometry
AAE 451 – Team 5February 8, 2005 12
Future Work
Finalized Airfoil Selection Aircraft Wetted Area Tail Geometry Aerodynamic Mathematical Model Control Surfaces