FX 79-L-100 (fx79l100-il)
FX 79-L-100 - Wortmann FX 79-L-100 symmetrical airfoil
| Details | Dat file | Parser | |
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(fx79l100-il) FX 79-L-100 Wortmann FX 79-L-100 symmetrical airfoil Max thickness 10.1% at 33.9% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
FX 79-L-100 1.00000 0.00000 0.99893 0.00090 0.99572 0.00114 0.99039 0.00156 0.98296 0.00202 0.97347 0.00266 0.96194 0.00343 0.94844 0.00435 0.93301 0.00541 0.91573 0.00662 0.89668 0.00800 0.87592 0.00958 0.85355 0.01136 0.82967 0.01334 0.80438 0.01553 0.77779 0.01790 0.75000 0.02046 0.72114 0.02318 0.69134 0.02605 0.66072 0.02903 0.62941 0.03208 0.59755 0.03515 0.56526 0.03816 0.53270 0.04102 0.50000 0.04362 0.46730 0.04588 0.43474 0.04771 0.40245 0.04907 0.37059 0.04995 0.33928 0.05033 0.30866 0.05023 0.27886 0.04970 0.25000 0.04880 0.22221 0.04754 0.19562 0.04596 0.17033 0.04408 0.14645 0.04193 0.12408 0.03953 0.10332 0.03690 0.08427 0.03406 0.06699 0.03101 0.05156 0.02779 0.03806 0.02438 0.02653 0.02076 0.01704 0.01691 0.00961 0.01284 0.00428 0.00860 0.00107 0.00431 0.00000 0.00000 0.00107 -0.00431 0.00428 -0.00860 0.00961 -0.01284 0.01704 -0.01691 0.02653 -0.02076 0.03806 -0.02438 0.05156 -0.02779 0.06699 -0.03101 0.08427 -0.03406 0.10332 -0.03690 0.12408 -0.03953 0.14645 -0.04193 0.17033 -0.04408 0.19562 -0.04596 0.22221 -0.04754 0.25000 -0.04880 0.27886 -0.04970 0.30866 -0.05023 0.33928 -0.05033 0.37059 -0.04995 0.40245 -0.04907 0.43474 -0.04771 0.46730 -0.04588 0.50000 -0.04362 0.53270 -0.04102 0.56526 -0.03816 0.59755 -0.03515 0.62941 -0.03208 0.66072 -0.02903 0.69134 -0.02605 0.72114 -0.02318 0.75000 -0.02046 0.77779 -0.01790 0.80438 -0.01553 0.82967 -0.01334 0.85355 -0.01136 0.87592 -0.00958 0.89668 -0.00800 0.91573 -0.00662 0.93301 -0.00541 0.94844 -0.00435 0.96194 -0.00343 0.97347 -0.00266 0.98296 -0.00202 0.99039 -0.00156 0.99572 -0.00114 0.99893 -0.00090 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 79-L-100 (fx79l100-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx79l100-il | 50,000 | 9 | 27.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79l100-il | 50,000 | 5 | 27 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79l100-il | 100,000 | 9 | 38.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79l100-il | 100,000 | 5 | 35.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79l100-il | 200,000 | 9 | 50.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79l100-il | 200,000 | 5 | 41.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79l100-il | 500,000 | 9 | 58 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79l100-il | 500,000 | 5 | 58.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79l100-il | 1,000,000 | 9 | 70.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79l100-il | 1,000,000 | 5 | 72.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||