LWK 80-100 (lwk80100-il)
LWK 80-100 - LWK 80-100 symmetrical airfoil
| Details | Dat file | Parser | |
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(lwk80100-il) LWK 80-100 LWK 80-100 symmetrical airfoil Max thickness 10.1% at 40.2% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
LWK 80-100 1.00000 0.00000 0.99893 0.00080 0.99572 0.00110 0.99039 0.00161 0.98296 0.00221 0.97347 0.00299 0.96194 0.00392 0.94844 0.00505 0.93301 0.00641 0.91573 0.00804 0.89668 0.00999 0.87592 0.01227 0.85355 0.01491 0.82967 0.01792 0.80438 0.02129 0.77779 0.02491 0.75000 0.02865 0.72114 0.03238 0.69134 0.03596 0.66072 0.03928 0.62941 0.04221 0.59755 0.04466 0.56526 0.04662 0.53270 0.04811 0.50000 0.04918 0.46730 0.04988 0.43474 0.05025 0.40245 0.05031 0.37059 0.05007 0.33928 0.04956 0.30866 0.04877 0.27886 0.04773 0.25000 0.04645 0.22221 0.04492 0.19562 0.04317 0.17033 0.04121 0.14645 0.03904 0.12408 0.03669 0.10332 0.03415 0.08427 0.03144 0.06699 0.02857 0.05156 0.02553 0.03806 0.02230 0.02653 0.01884 0.01704 0.01517 0.00961 0.01136 0.00428 0.00747 0.00107 0.00370 0.00000 0.00001 0.00107 -0.00370 0.00428 -0.00750 0.00961 -0.01139 0.01704 -0.01521 0.02653 -0.01885 0.03806 -0.02229 0.05156 -0.02553 0.06699 -0.02857 0.08427 -0.03144 0.10332 -0.03415 0.12408 -0.03669 0.14645 -0.03904 0.17033 -0.04121 0.19562 -0.04317 0.22221 -0.04492 0.25000 -0.04645 0.27886 -0.04773 0.30866 -0.04877 0.33928 -0.04956 0.37059 -0.05007 0.40245 -0.05031 0.43474 -0.05025 0.46730 -0.04988 0.50000 -0.04918 0.53270 -0.04811 0.56526 -0.04662 0.59755 -0.04466 0.62941 -0.04221 0.66072 -0.03928 0.69134 -0.03596 0.72114 -0.03238 0.75000 -0.02865 0.77779 -0.02491 0.80438 -0.02129 0.82967 -0.01792 0.85355 -0.01491 0.87592 -0.01227 0.89668 -0.00999 0.91573 -0.00804 0.93301 -0.00641 0.94844 -0.00505 0.96194 -0.00392 0.97347 -0.00299 0.98296 -0.00221 0.99039 -0.00161 0.99572 -0.00110 0.99893 -0.00080 1.00000 0.00000 |
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Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
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Polars for LWK 80-100 (lwk80100-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| lwk80100-il | 50,000 | 9 | 26.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk80100-il | 50,000 | 5 | 26.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk80100-il | 100,000 | 9 | 59.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk80100-il | 100,000 | 5 | 31.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk80100-il | 200,000 | 9 | 44 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk80100-il | 200,000 | 5 | 38.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk80100-il | 500,000 | 9 | 49 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk80100-il | 500,000 | 5 | 51.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk80100-il | 1,000,000 | 9 | 60.5 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk80100-il | 1,000,000 | 5 | 61.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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