FX 61-140 AIRFOIL (fx61140-il)
FX 61-140 AIRFOIL - Wortmann FX 61-140 airfoil
| Details | Dat file | Parser | |
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(fx61140-il) FX 61-140 AIRFOIL Wortmann FX 61-140 airfoil Max thickness 14% at 33.9% chord. Max camber 2.5% at 30.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
FX 61-140 AIRFOIL
49. 49.
0.0000000 0.0000000
0.0010700 0.0050400
0.0042800 0.0107200
0.0096100 0.0167800
0.0170400 0.0231400
0.0265300 0.0298800
0.0380600 0.0368400
0.0515600 0.0437800
0.0669900 0.0507000
0.0842700 0.0574200
0.1033200 0.0639300
0.1240800 0.0700500
0.1464500 0.0757500
0.1703300 0.0808100
0.1956200 0.0852100
0.2222100 0.0887700
0.2500000 0.0915200
0.2788600 0.0933600
0.3086600 0.0943500
0.3392800 0.0944400
0.3705900 0.0936800
0.4024500 0.0921100
0.4347400 0.0898600
0.4673000 0.0870400
0.5000000 0.0837600
0.5327000 0.0801400
0.5652600 0.0762200
0.5975500 0.0720700
0.6294100 0.0677800
0.6607200 0.0633800
0.6913400 0.0589300
0.7211400 0.0544600
0.7500000 0.0500000
0.7777900 0.0456100
0.8043801 0.0413000
0.8296700 0.0370900
0.8535500 0.0330200
0.8759201 0.0290900
0.8966800 0.0253200
0.9157300 0.0217300
0.9330100 0.0183100
0.9484400 0.0150500
0.9619400 0.0119400
0.9734700 0.0089700
0.9829600 0.0062200
0.9903900 0.0039400
0.9957200 0.0020100
0.9989300 0.0005800
1.0000000 0.0000000
0.0000000 0.0000000
0.0010700 -.0019800
0.0042800 -.0049100
0.0096100 -.0080400
0.0170400 -.0112200
0.0265300 -.0145400
0.0380600 -.0177800
0.0515600 -.0209800
0.0669900 -.0241300
0.0842700 -.0272100
0.1033200 -.0301600
0.1240800 -.0329400
0.1464500 -.0355300
0.1703300 -.0378800
0.1956200 -.0399600
0.2222100 -.0417600
0.2500000 -.0432400
0.2788600 -.0443500
0.3086600 -.0450900
0.3392800 -.0453900
0.3705900 -.0452400
0.4024500 -.0445900
0.4347400 -.0434400
0.4673000 -.0416700
0.5000000 -.0393500
0.5327000 -.0364300
0.5652600 -.0329700
0.5975500 -.0288700
0.6294100 -.0241500
0.6607200 -.0189000
0.6913400 -.0134400
0.7211400 -.0081000
0.7500000 -.0032600
0.7777900 0.0009400
0.8043801 0.0043800
0.8296700 0.0071000
0.8535500 0.0090500
0.8759201 0.0103100
0.8966800 0.0109000
0.9157300 0.0109100
0.9330100 0.0103800
0.9484400 0.0093900
0.9619400 0.0079800
0.9734700 0.0062800
0.9829600 0.0044500
0.9903900 0.0029100
0.9957200 0.0014600
0.9989300 0.0003000
1.0000000 0.0000000
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Polars for FX 61-140 AIRFOIL (fx61140-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx61140-il | 50,000 | 9 | 14.4 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61140-il | 50,000 | 5 | 31.2 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61140-il | 100,000 | 9 | 51.6 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61140-il | 100,000 | 5 | 52 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61140-il | 200,000 | 9 | 69.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61140-il | 200,000 | 5 | 70.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61140-il | 500,000 | 9 | 96.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61140-il | 500,000 | 5 | 96.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61140-il | 1,000,000 | 9 | 119 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61140-il | 1,000,000 | 5 | 115.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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