FX 63-145 AIRFOIL (fx63145-il)
FX 63-145 AIRFOIL - Wortmann FX 63-145 airfoil
| Details | Dat file | Parser | |
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(fx63145-il) FX 63-145 AIRFOIL Wortmann FX 63-145 airfoil Max thickness 14.5% at 30.9% chord. Max camber 4% at 37.1% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
FX 63-145 AIRFOIL
49. 49.
0.0000000 0.0000000
0.0010200 0.0065000
0.0042200 0.0160000
0.0096000 0.0240000
0.0170200 0.0320000
0.0265000 0.0405000
0.0380200 0.0490000
0.0515800 0.0569900
0.0669400 0.0669800
0.0842200 0.0729200
0.1033000 0.0813100
0.1240300 0.0864700
0.1464300 0.0934200
0.1703700 0.0975800
0.1955800 0.1029100
0.2222100 0.1057500
0.2499800 0.1092600
0.2789100 0.1105000
0.3085100 0.1120700
0.3393300 0.1115400
0.3705600 0.1110300
0.4024300 0.1086000
0.4346900 0.1059900
0.4673300 0.1017500
0.4999700 0.0975200
0.5327400 0.0923600
0.5652500 0.0874100
0.5975000 0.0819100
0.6293800 0.0765200
0.6607400 0.0709500
0.6913300 0.0656500
0.7211500 0.0601400
0.7499501 0.0549800
0.7777300 0.0497700
0.8043500 0.0448800
0.8297000 0.0400700
0.8535000 0.0355300
0.8759000 0.0310400
0.8964400 0.0268600
0.9157100 0.0228500
0.9329900 0.0191400
0.9484800 0.0156400
0.9619200 0.0123700
0.9734400 0.0093100
0.9829100 0.0065000
0.9903400 0.0041100
0.9957100 0.0021900
0.9989100 0.0009000
1.0000000 0.0000000
0.0000000 0.0000000
0.0010200 -.0020000
0.0042200 -.0040000
0.0096000 -.0070000
0.0170200 -.0097000
0.0265000 -.0131100
0.0380200 -.0150000
0.0515800 -.0184700
0.0669400 -.0206000
0.0842200 -.0239000
0.1033000 -.0252300
0.1240300 -.0284100
0.1464300 -.0293200
0.1703700 -.0316700
0.1955800 -.0320700
0.2222100 -.0335400
0.2499800 -.0332400
0.2789100 -.0337100
0.3085100 -.0326400
0.3393300 -.0321100
0.3705600 -.0302400
0.4024300 -.0287600
0.4346900 -.0261300
0.4673300 -.0237500
0.4999700 -.0203500
0.5327400 -.0171000
0.5652500 -.0129500
0.5975000 -.0090600
0.6293800 -.0048400
0.6607400 -.0012600
0.6913300 0.0022400
0.7211500 0.0050100
0.7499501 0.0076000
0.7777300 0.0094600
0.8043500 0.0110700
0.8297000 0.0120200
0.8535000 0.0126500
0.8759000 0.0126700
0.8964400 0.0124300
0.9157100 0.0117000
0.9329900 0.0107200
0.9484800 0.0094100
0.9619200 0.0078500
0.9734400 0.0060400
0.9829100 0.0041200
0.9903400 0.0023800
0.9957100 0.0009700
0.9989100 0.0001100
1.0000000 0.0000000
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Polars for FX 63-145 AIRFOIL (fx63145-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx63145-il | 50,000 | 9 | 13.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63145-il | 50,000 | 5 | 33.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63145-il | 100,000 | 9 | 56.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63145-il | 100,000 | 5 | 56.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63145-il | 200,000 | 9 | 75.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63145-il | 200,000 | 5 | 59.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63145-il | 500,000 | 9 | 75.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63145-il | 500,000 | 5 | 72.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63145-il | 1,000,000 | 9 | 86.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63145-il | 1,000,000 | 5 | 81.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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