WORTMANN FX 2 AIRFOIL (fx2-il)
WORTMANN FX 2 AIRFOIL - Wortmann FX 2 airfoil
| Details | Dat file | Parser | |
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(fx2-il) WORTMANN FX 2 AIRFOIL Wortmann FX 2 airfoil Max thickness 20.4% at 43.5% chord. Max camber 3.8% at 69.1% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
WORTMANN FX 2 AIRFOIL
24.0 24.0
0.0000000 0.0000000
0.0170400 0.0255600
0.0380600 0.0404600
0.0669900 0.0548100
0.1033300 0.0698000
0.1464400 0.0836600
0.1956200 0.0965700
0.2500000 0.1079700
0.3086600 0.1173000
0.3705900 0.1242400
0.4347400 0.1286100
0.5000000 0.1301500
0.5652600 0.1284200
0.6294100 0.1232500
0.6913400 0.1140100
0.7500000 0.0982500
0.8043800 0.0767100
0.8535600 0.0564400
0.8966700 0.0386100
0.9330100 0.0246500
0.9616400 0.0143900
0.9829600 0.0067800
0.9957200 0.0021400
1.0000000 0.0000000
0.0000000 0.0000000
0.0170400 -.0186900
0.0380600 -.0287600
0.0669900 -.0375200
0.1033300 -.0467500
0.1464400 -.0549200
0.1956200 -.0622200
0.2500000 -.0684000
0.3086600 -.0729700
0.3705900 -.0755300
0.4347400 -.0758500
0.5000000 -.0729900
0.5652600 -.0653800
0.6294100 -.0547000
0.6913400 -.0385600
0.7500000 -.0241600
0.8043800 -.0133100
0.8535600 -.0045900
0.8966700 0.0000700
0.9330100 0.0026500
0.9616400 0.0027800
0.9829600 0.0020400
0.9957200 0.0005700
1.0000000 0.0000000
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Polars for WORTMANN FX 2 AIRFOIL (fx2-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx2-il | 50,000 | 9 | 18 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx2-il | 50,000 | 5 | 14.9 at α=12.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx2-il | 100,000 | 9 | 23.7 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx2-il | 100,000 | 5 | 22.7 at α=11° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx2-il | 200,000 | 9 | 34.2 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx2-il | 200,000 | 5 | 34.1 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx2-il | 500,000 | 9 | 51.6 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx2-il | 500,000 | 5 | 50.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx2-il | 1,000,000 | 9 | 107.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx2-il | 1,000,000 | 5 | 111 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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