FX 63-143 AIRFOIL (fx63143-il)
FX 63-143 AIRFOIL - Wortmann FX 63-143 airfoil
| Details | Dat file | Parser | |
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(fx63143-il) FX 63-143 AIRFOIL Wortmann FX 63-143 airfoil Max thickness 14.3% at 33.9% chord. Max camber 3.1% at 30.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
FX 63-143 AIRFOIL
49. 49.
0.0000000 0.0000000
0.0010200 0.0055000
0.0042200 0.0118900
0.0096000 0.0180000
0.0170200 0.0250300
0.0265000 0.0322000
0.0380200 0.0396300
0.0515800 0.0459900
0.0669400 0.0543900
0.0842200 0.0607200
0.1033000 0.0684900
0.1240300 0.0743700
0.1464300 0.0811100
0.1703700 0.0860700
0.1955800 0.0914100
0.2222100 0.0950100
0.2499800 0.0985800
0.2789100 0.1005200
0.3086100 0.1021200
0.3393300 0.1021700
0.3705600 0.1016600
0.4024300 0.0997100
0.4346900 0.0971600
0.4673300 0.0934700
0.4999700 0.0893000
0.5327400 0.0844200
0.5662500 0.0794300
0.5975000 0.0740600
0.6293800 0.0686600
0.6607400 0.0631100
0.6913300 0.0577300
0.7211500 0.0523100
0.7499501 0.0472000
0.7777300 0.0421700
0.8043500 0.0374700
0.8297000 0.0329800
0.8535000 0.0288100
0.8759000 0.0249100
0.8964400 0.0213200
0.9157100 0.0180100
0.9329900 0.0149700
0.9484800 0.0121700
0.9619200 0.0095500
0.9734400 0.0070800
0.9829100 0.0048200
0.9903400 0.0028800
0.9957100 0.0013600
0.9989100 0.0003900
1.0000000 0.0000000
0.0000000 0.0000000
0.0010200 -.0030000
0.0042200 -.0051500
0.0096000 -.0098100
0.0170200 -.0115900
0.0265000 -.0157600
0.0380200 -.0176200
0.0515800 -.0212300
0.0669400 -.0229500
0.0842200 -.0261400
0.1033000 -.0278500
0.1240300 -.0307100
0.1464300 -.0322900
0.1703700 -.0347500
0.1955800 -.0368000
0.2222100 -.0379200
0.2499800 -.0387600
0.2789100 -.0400500
0.3086100 -.0403800
0.3393300 -.0410200
0.3705600 -.0408100
0.4024300 -.0408300
0.4346900 -.0401300
0.4673300 -.0396200
0.4999700 -.0385000
0.5327400 -.0375100
0.5662500 -.0360100
0.5975000 -.0346100
0.6293800 -.0327900
0.6607400 -.0310200
0.6913300 -.0288700
0.7211500 -.0267300
0.7499501 -.0241800
0.7777300 -.0215800
0.8043500 -.0186800
0.8297000 -.0156800
0.8535000 -.0124200
0.8759000 -.0090800
0.8964400 -.0056700
0.9157100 -.0026400
0.9329900 -.0001800
0.9484800 0.0015000
0.9619200 0.0024400
0.9734400 0.0026700
0.9829100 0.0023500
0.9903400 0.0017000
0.9957100 0.0008900
0.9989100 0.0003000
1.0000000 0.0000000
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Polars for FX 63-143 AIRFOIL (fx63143-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx63143-il | 50,000 | 9 | 10.7 at α=-1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63143-il | 50,000 | 5 | 24 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63143-il | 100,000 | 9 | 46.5 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63143-il | 100,000 | 5 | 49.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63143-il | 200,000 | 9 | 72.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63143-il | 200,000 | 5 | 65.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63143-il | 500,000 | 9 | 71 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63143-il | 500,000 | 5 | 64.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63143-il | 1,000,000 | 9 | 79.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63143-il | 1,000,000 | 5 | 78.7 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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