FX 68-H-120 (fx68h120-il)
FX 68-H-120 - Wortmann FX 68-H-120 airfoil
| Details | Dat file | Parser | |
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(fx68h120-il) FX 68-H-120 Wortmann FX 68-H-120 airfoil Max thickness 11.8% at 25% chord. Max camber 2.3% at 33.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
FX 68-H-120 1.00000 0.00000 0.99893 0.00006 0.99572 0.00003 0.99039 0.00020 0.98296 0.00057 0.97347 0.00127 0.96194 0.00240 0.94844 0.00405 0.93301 0.00628 0.91573 0.00912 0.89668 0.01253 0.87592 0.01646 0.85355 0.02088 0.82967 0.02576 0.80438 0.03098 0.77779 0.03637 0.75000 0.04176 0.72114 0.04703 0.69134 0.05208 0.66072 0.05678 0.62941 0.06102 0.59755 0.06475 0.56526 0.06797 0.53270 0.07075 0.50000 0.07319 0.46730 0.07536 0.43474 0.07726 0.40245 0.07887 0.37059 0.08017 0.33928 0.08112 0.30866 0.08170 0.27886 0.08187 0.25000 0.08157 0.22221 0.08074 0.19562 0.07935 0.17033 0.07734 0.14645 0.07471 0.12408 0.07138 0.10332 0.06717 0.08427 0.06183 0.06699 0.05520 0.05156 0.04742 0.03806 0.03890 0.02653 0.03013 0.01704 0.02171 0.00961 0.01423 0.00428 0.00819 0.00107 0.00362 0.00000 0.00000 0.00107 -0.00338 0.00428 -0.00700 0.00961 -0.01096 0.01704 -0.01511 0.02653 -0.01927 0.03806 -0.02327 0.05156 -0.02698 0.06699 -0.03023 0.08427 -0.03283 0.10332 -0.03466 0.12408 -0.03578 0.14645 -0.03640 0.17033 -0.03672 0.19562 -0.03684 0.22221 -0.03676 0.25000 -0.03650 0.27886 -0.03609 0.30866 -0.03554 0.33928 -0.03486 0.37059 -0.03407 0.40245 -0.03317 0.43474 -0.03217 0.46730 -0.03110 0.50000 -0.02996 0.53270 -0.02877 0.56526 -0.02753 0.59755 -0.02625 0.62941 -0.02495 0.66072 -0.02361 0.69134 -0.02225 0.72114 -0.02086 0.75000 -0.01945 0.77779 -0.01802 0.80438 -0.01656 0.82967 -0.01509 0.85355 -0.01359 0.87592 -0.01207 0.89668 -0.01054 0.91573 -0.00900 0.93301 -0.00747 0.94844 -0.00598 0.96194 -0.00459 0.97347 -0.00335 0.98296 -0.00230 0.99039 -0.00144 0.99572 -0.00077 0.99893 -0.00030 1.00000 0.00000 |
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
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Polars for FX 68-H-120 (fx68h120-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx68h120-il | 50,000 | 9 | 28.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx68h120-il | 50,000 | 5 | 29.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx68h120-il | 100,000 | 9 | 40.2 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx68h120-il | 100,000 | 5 | 41 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx68h120-il | 200,000 | 9 | 54.5 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx68h120-il | 200,000 | 5 | 54.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx68h120-il | 500,000 | 9 | 74.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx68h120-il | 500,000 | 5 | 73.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx68h120-il | 1,000,000 | 9 | 91.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx68h120-il | 1,000,000 | 5 | 88.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||