FX74_CL5_140 (fx74cl5140-il)
FX74_CL5_140 - Wortmann FX 74-CL5-140 high lift airfoil
| Details | Dat file | Parser | |
|
(fx74cl5140-il) FX74_CL5_140 Wortmann FX 74-CL5-140 high lift airfoil Max thickness 14% at 30.9% chord. Max camber 9.9% at 37.1% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
FX74_CL5_140 1.00000 0.00000 0.99893 0.00082 0.99039 0.00597 0.97347 0.01407 0.94844 0.02405 0.91573 0.03570 0.87592 0.04881 0.85355 0.05583 0.82967 0.06317 0.80438 0.07069 0.77779 0.07846 0.75000 0.08629 0.72114 0.09429 0.69134 0.10223 0.66072 0.11027 0.62941 0.11807 0.59755 0.12594 0.56526 0.13353 0.53270 0.14101 0.50000 0.14801 0.46730 0.15471 0.43474 0.16051 0.40245 0.16524 0.37059 0.16780 0.33920 0.16855 0.30866 0.16720 0.27866 0.16424 0.25000 0.15959 0.22221 0.15361 0.19562 0.14610 0.17033 0.13754 0.14645 0.12791 0.12408 0.11763 0.10332 0.10650 0.08427 0.09512 0.06699 0.08329 0.05156 0.07146 0.03806 0.05954 0.02653 0.04801 0.01704 0.03661 0.00961 0.02628 0.00426 0.01727 0.00107 0.00936 0.00000 0.00000 0.00107 -.00366 0.00426 -.00689 0.00961 -.00684 0.01704 -.00632 0.02653 -.00587 0.03806 -.00496 0.05156 -.00349 0.06699 -.00130 0.08427 0.00120 0.10332 0.00406 0.12408 0.00695 0.14645 0.01002 0.17033 0.01297 0.19562 0.01599 0.22221 0.01884 0.25000 0.02170 0.27866 0.02424 0.30866 0.02673 0.33920 0.02886 0.37059 0.03092 0.40245 0.03259 0.43474 0.03422 0.46730 0.03549 0.50000 0.03682 0.53270 0.03791 0.56526 0.03910 0.59755 0.04013 0.62941 0.04162 0.66072 0.04306 0.69134 0.04440 0.72114 0.04498 0.75000 0.04493 0.77779 0.04400 0.80438 0.04242 0.82967 0.04012 0.85355 0.03733 0.87592 0.03402 0.91573 0.02640 0.94844 0.01824 0.97347 0.01052 0.99039 0.00444 0.99893 0.00065 1.00000 0.00000 |
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for FX74_CL5_140 (fx74cl5140-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx74cl5140-il | 50,000 | 9 | 6.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl5140-il | 50,000 | 5 | 18.3 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl5140-il | 100,000 | 9 | 33.1 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl5140-il | 100,000 | 5 | 46.8 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl5140-il | 200,000 | 9 | 72.7 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl5140-il | 200,000 | 5 | 73.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl5140-il | 500,000 | 9 | 118.8 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl5140-il | 500,000 | 5 | 115.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl5140-il | 1,000,000 | 9 | 156.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl5140-il | 1,000,000 | 5 | 149.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||