FX 60-100 AIRFOIL (fx60100-il)
FX 60-100 AIRFOIL - Wortmann FX 60-100 airfoil
| Details | Dat file | Parser | |
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(fx60100-il) FX 60-100 AIRFOIL Wortmann FX 60-100 airfoil Max thickness 10% at 27.9% chord. Max camber 3.6% at 56.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
FX 60-100 AIRFOIL
49. 49.
0.0000000 0.0000000
0.0010700 0.0057400
0.0042800 0.0114400
0.0096100 0.0177500
0.0170400 0.0236800
0.0265300 0.0294800
0.0380600 0.0352300
0.0515600 0.0405600
0.0669900 0.0460900
0.0842700 0.0508600
0.1033200 0.0556900
0.1240800 0.0598900
0.1464500 0.0640400
0.1703300 0.0675400
0.1956200 0.0708100
0.2222100 0.0733900
0.2500000 0.0756500
0.2788600 0.0772000
0.3086600 0.0783800
0.3392800 0.0788800
0.3705900 0.0789800
0.4024500 0.0784500
0.4347400 0.0775000
0.4673000 0.0759600
0.5000000 0.0740900
0.5327000 0.0717400
0.5652600 0.0691100
0.5975500 0.0660800
0.6294100 0.0627500
0.6607200 0.0590500
0.6913400 0.0551100
0.7211400 0.0508900
0.7500000 0.0465200
0.7777900 0.0420000
0.8043801 0.0374700
0.8296700 0.0329800
0.8535500 0.0286400
0.8759201 0.0244700
0.8966800 0.0205300
0.9157300 0.0168100
0.9330100 0.0134200
0.9484400 0.0103500
0.9619400 0.0076600
0.9734700 0.0053400
0.9829600 0.0034100
0.9903900 0.0019300
0.9957200 0.0008600
0.9989300 0.0002300
1.0000000 0.0000000
0.0000000 0.0000000
0.0010700 -.0020000
0.0042800 -.0043600
0.0096100 -.0069100
0.0170400 -.0097000
0.0265300 -.0124700
0.0380600 -.0148100
0.0515600 -.0173000
0.0669900 -.0191300
0.0842700 -.0211000
0.1033200 -.0224600
0.1240800 -.0237700
0.1464500 -.0244700
0.1703300 -.0250300
0.1956200 -.0250000
0.2222100 -.0247500
0.2500000 -.0238900
0.2788600 -.0227500
0.3086600 -.0210000
0.3392800 -.0189500
0.3705900 -.0163700
0.4024500 -.0135700
0.4347400 -.0104500
0.4673000 -.0073100
0.5000000 -.0040500
0.5327000 -.0009200
0.5652600 0.0021700
0.5975500 0.0049600
0.6294100 0.0074800
0.6607200 0.0095100
0.6913400 0.0111800
0.7211400 0.0124100
0.7500000 0.0132900
0.7777900 0.0137300
0.8043801 0.0138100
0.8296700 0.0134700
0.8535500 0.0128000
0.8759201 0.0118600
0.8966800 0.0107200
0.9157300 0.0094100
0.9330100 0.0080200
0.9484400 0.0065900
0.9619400 0.0051500
0.9734700 0.0037700
0.9829600 0.0025100
0.9903900 0.0015100
0.9957200 0.0007000
0.9989300 0.0001500
1.0000000 0.0000000
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Polars for FX 60-100 AIRFOIL (fx60100-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx60100-il | 50,000 | 9 | 40.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60100-il | 50,000 | 5 | 42.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60100-il | 100,000 | 9 | 62.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60100-il | 100,000 | 5 | 61.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60100-il | 200,000 | 9 | 84.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60100-il | 200,000 | 5 | 77.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60100-il | 500,000 | 9 | 109.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60100-il | 500,000 | 5 | 87.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60100-il | 1,000,000 | 9 | 112.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60100-il | 1,000,000 | 5 | 96.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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