FX60-100 10.0% smoothed (fx60100sm-il)
FX60-100 10.0% smoothed - Wortmann FX 60-100 airfoil (smoothed)
| Details | Dat file | Parser | |
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(fx60100sm-il) FX60-100 10.0% smoothed Wortmann FX 60-100 airfoil (smoothed) Max thickness 10% at 27.9% chord. Max camber 3.5% at 56.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
FX60-100 10.0% smoothed 1.00000 0.0 0.99572 0.00087 0.98296 0.00344 0.96194 0.00765 0.93301 0.01342 0.89668 0.02056 0.85355 0.02875 0.80438 0.03754 0.75000 0.04643 0.69134 0.05491 0.62941 0.06255 0.56526 0.06902 0.50000 0.07402 0.43474 0.07735 0.37059 0.07880 0.33928 0.07876 0.30866 0.07819 0.27886 0.07708 0.25000 0.07543 0.22221 0.07326 0.19562 0.07059 0.17033 0.06743 0.14645 0.06383 0.12408 0.05982 0.10332 0.05545 0.08427 0.05078 0.06699 0.04584 0.05156 0.04064 0.03806 0.03517 0.02653 0.02937 0.01704 0.02331 0.00961 0.01715 0.00428 0.01123 0.00107 0.00589 0.0 0.00142 0.00107 -0.00216 0.00428 -0.00503 0.00961 -0.00751 0.01704 -0.00991 0.02653 -0.01235 0.03806 -0.01482 0.05156 -0.01719 0.06699 -0.01933 0.08427 -0.02115 0.10332 -0.02265 0.12408 -0.02381 0.14645 -0.02464 0.17033 -0.02510 0.19562 -0.02518 0.22221 -0.02483 0.25000 -0.02402 0.27886 -0.02273 0.30866 -0.02096 0.33928 -0.01874 0.37059 -0.01617 0.43474 -0.01029 0.50000 -0.00404 0.56526 0.00192 0.62941 0.00702 0.69134 0.01081 0.75000 0.01305 0.80438 0.01367 0.85355 0.01281 0.89668 0.01080 0.93301 0.00808 0.96194 0.00514 0.98296 0.00250 0.99572 0.00066 1.00000 0.0 |
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
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Polars for FX60-100 10.0% smoothed (fx60100sm-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx60100sm-il | 50,000 | 9 | 40.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60100sm-il | 50,000 | 5 | 42.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60100sm-il | 100,000 | 9 | 62.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60100sm-il | 100,000 | 5 | 61.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60100sm-il | 200,000 | 9 | 85.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60100sm-il | 200,000 | 5 | 79.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60100sm-il | 500,000 | 9 | 112.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60100sm-il | 500,000 | 5 | 91.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60100sm-il | 1,000,000 | 9 | 120.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60100sm-il | 1,000,000 | 5 | 100.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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