FX 61-163 AIRFOIL (fx61163-il)
FX 61-163 AIRFOIL - Wortmann FX 61-163 airfoil
| Details | Dat file | Parser | |
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(fx61163-il) FX 61-163 AIRFOIL Wortmann FX 61-163 airfoil Max thickness 16.4% at 37.1% chord. Max camber 2.6% at 33.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
FX 61-163 AIRFOIL
49. 49.
0.0000000 0.0000000
0.0010200 0.0056600
0.0042200 0.0123400
0.0096000 0.0192500
0.0170200 0.0264100
0.0265000 0.0340200
0.0380200 0.0417500
0.0515800 0.0492900
0.0669400 0.0568700
0.0842200 0.0641200
0.1033000 0.0710900
0.1240300 0.0776000
0.1464300 0.0837100
0.1703700 0.0892400
0.1955800 0.0942200
0.2222100 0.0984400
0.2499800 0.1019400
0.2789100 0.1045500
0.3086100 0.1063500
0.3393300 0.1072300
0.3705600 0.1072800
0.4024300 0.1063900
0.4346900 0.1045700
0.4673300 0.1016800
0.4999700 0.0978000
0.5327400 0.0930300
0.5652500 0.0877200
0.5975000 0.0820800
0.6293800 0.0763700
0.6607400 0.0706400
0.6913300 0.0649700
0.7211500 0.0593500
0.7499501 0.0538800
0.7777300 0.0485600
0.8043500 0.0434700
0.8297000 0.0386100
0.8535000 0.0340300
0.8759000 0.0296800
0.8964400 0.0256000
0.9157100 0.0217600
0.9329900 0.0181700
0.9484800 0.0148100
0.9619200 0.0116700
0.9734400 0.0087500
0.9829100 0.0061000
0.9903400 0.0039000
0.9957100 0.0020600
0.9989100 0.0006900
1.0000000 0.0000000
0.0000000 0.0000000
0.0010200 -.0024800
0.0042200 -.0056000
0.0096000 -.0090700
0.0170200 -.0127200
0.0265000 -.0165600
0.0380200 -.0202700
0.0515800 -.0241200
0.0669400 -.0278600
0.0842200 -.0316000
0.1033000 -.0351800
0.1240300 -.0387000
0.1464300 -.0419900
0.1703700 -.0451100
0.1955800 -.0479200
0.2222100 -.0504400
0.2499800 -.0525200
0.2789100 -.0542100
0.3086100 -.0553700
0.3393300 -.0560900
0.3705600 -.0562500
0.4024300 -.0558500
0.4346900 -.0547400
0.4673300 -.0529300
0.4999700 -.0503900
0.5327400 -.0471900
0.5652500 -.0432400
0.5975000 -.0384500
0.6293800 -.0328800
0.6607400 -.0268500
0.6913300 -.0207900
0.7211500 -.0151700
0.7499501 -.0101400
0.7777300 -.0057600
0.8043500 -.0020100
0.8297000 0.0011000
0.8535000 0.0035800
0.8759000 0.0054200
0.8964400 0.0066700
0.9157100 0.0073400
0.9329900 0.0074900
0.9484800 0.0071500
0.9619200 0.0063700
0.9734400 0.0052600
0.9829100 0.0039200
0.9903400 0.0027300
0.9957100 0.0015000
0.9989100 0.0004400
1.0000000 0.0000000
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Polars for FX 61-163 AIRFOIL (fx61163-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx61163-il | 50,000 | 9 | 6.1 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61163-il | 50,000 | 5 | 19.4 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61163-il | 100,000 | 9 | 47.7 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61163-il | 100,000 | 5 | 50 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61163-il | 200,000 | 9 | 70.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61163-il | 200,000 | 5 | 72.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61163-il | 500,000 | 9 | 103.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61163-il | 500,000 | 5 | 98.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61163-il | 1,000,000 | 5 | 115.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61163-il | 1,000,000 | 0 | 127.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
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