FX 69-PR-281 (fx69pr281-il)
FX 69-PR-281 - Wortmann FX 69-PR-281 airfoil
| Details | Dat file | Parser | |
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(fx69pr281-il) FX 69-PR-281 Wortmann FX 69-PR-281 airfoil Max thickness 28.1% at 22.2% chord. Max camber 5.6% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
FX 69-PR-281 1.00000 0.00000 0.99893 0.00086 0.99572 0.00291 0.99039 0.00571 0.98296 0.00930 0.97347 0.01357 0.96194 0.01842 0.94844 0.02386 0.93301 0.02990 0.91573 0.03643 0.89668 0.04320 0.87592 0.05071 0.85355 0.05857 0.82967 0.06671 0.80438 0.07529 0.77779 0.08414 0.75000 0.09314 0.72114 0.10214 0.69134 0.11114 0.66072 0.12000 0.62941 0.12886 0.59755 0.13729 0.56526 0.14529 0.53270 0.15286 0.50000 0.15986 0.46730 0.16614 0.43474 0.17186 0.40245 0.17657 0.37059 0.18029 0.33928 0.18286 0.30866 0.18457 0.27886 0.18514 0.25000 0.18457 0.22221 0.18286 0.19562 0.17957 0.17033 0.17486 0.14645 0.16871 0.12408 0.16100 0.10332 0.15186 0.08427 0.14129 0.06699 0.12929 0.05156 0.11600 0.03806 0.10186 0.02653 0.08700 0.01704 0.07157 0.00961 0.05571 0.00428 0.03886 0.00107 0.02043 0.00000 0.00000 0.00107 -0.01600 0.00428 -0.03000 0.00961 -0.04243 0.01704 -0.05371 0.02653 -0.06400 0.03806 -0.07300 0.05156 -0.08086 0.06699 -0.08757 0.08427 -0.09329 0.10332 -0.09771 0.12408 -0.10071 0.14645 -0.10229 0.17033 -0.10243 0.19562 -0.10100 0.22221 -0.09843 0.25000 -0.09486 0.27886 -0.09057 0.30866 -0.08557 0.33928 -0.08000 0.37059 -0.07386 0.40245 -0.06757 0.43474 -0.06100 0.46730 -0.05429 0.50000 -0.04757 0.53270 -0.04114 0.56526 -0.03486 0.59755 -0.02886 0.62941 -0.02314 0.66072 -0.01786 0.69134 -0.01314 0.72114 -0.00871 0.75000 -0.00486 0.77779 -0.00157 0.80438 0.00114 0.82967 0.00329 0.85355 0.00500 0.87592 0.00614 0.89668 0.00720 0.91573 0.00729 0.93301 0.00717 0.94844 0.00671 0.96194 0.00604 0.97347 0.00514 0.98296 0.00396 0.99039 0.00271 0.99572 0.00160 0.99893 0.00057 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 69-PR-281 (fx69pr281-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx69pr281-il | 50,000 | 9 | 3.4 at α=-5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69pr281-il | 50,000 | 5 | 6.4 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx69pr281-il | 100,000 | 9 | 21.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69pr281-il | 100,000 | 5 | 26.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx69pr281-il | 200,000 | 9 | 41.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69pr281-il | 200,000 | 5 | 35 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx69pr281-il | 500,000 | 9 | 49.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69pr281-il | 500,000 | 5 | 47.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx69pr281-il | 1,000,000 | 9 | 64.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69pr281-il | 1,000,000 | 5 | 61.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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