FX 73-K-170/22 (fx73k170-il)
FX 73-K-170/22 - Wortmann FX 73-K-170/22 airfoil for use with flaps (K)
| Details | Dat file | Parser | |
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(fx73k170-il) FX 73-K-170/22 Wortmann FX 73-K-170/22 airfoil for use with flaps (K) Max thickness 17.1% at 40.2% chord. Max camber 4.6% at 56.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
FX 73-K-170/22 1.00000 0.00000 0.99893 0.00138 0.99572 0.00263 0.99039 0.00438 0.98296 0.00651 0.97347 0.00910 0.96194 0.01213 0.94844 0.01563 0.93301 0.01963 0.91573 0.02419 0.89668 0.02943 0.87592 0.03538 0.85355 0.04209 0.82967 0.04953 0.80438 0.05765 0.77779 0.06636 0.75000 0.07543 0.72114 0.08451 0.69134 0.09320 0.66072 0.10109 0.62941 0.10805 0.59755 0.11416 0.56526 0.11933 0.53270 0.12352 0.50000 0.12656 0.46730 0.12843 0.43474 0.12924 0.40245 0.12899 0.37059 0.12776 0.33928 0.12562 0.30866 0.12262 0.27886 0.11879 0.25000 0.11420 0.22221 0.10890 0.19562 0.10297 0.17033 0.09648 0.14645 0.08950 0.12408 0.08210 0.10332 0.07436 0.08427 0.06635 0.06699 0.05817 0.05156 0.04992 0.03806 0.04168 0.02653 0.03359 0.01704 0.02580 0.00961 0.01845 0.00428 0.01147 0.00107 0.00517 0.00000 0.00000 0.00107 -0.00407 0.00428 -0.00742 0.00961 -0.01074 0.01704 -0.01419 0.02653 -0.01755 0.03806 -0.02081 0.05156 -0.02393 0.06699 -0.02691 0.08427 -0.02972 0.10332 -0.03233 0.12408 -0.03473 0.14645 -0.03688 0.17033 -0.03877 0.19562 -0.04037 0.22221 -0.04167 0.25000 -0.04264 0.27886 -0.04326 0.30866 -0.04351 0.33928 -0.04338 0.37059 -0.04281 0.40245 -0.04179 0.43474 -0.04024 0.46730 -0.03807 0.50000 -0.03525 0.53270 -0.03172 0.56526 -0.02750 0.59755 -0.02281 0.62941 -0.01796 0.66072 -0.01330 0.69134 -0.00906 0.72114 -0.00531 0.75000 -0.00211 0.77779 0.00055 0.80438 0.00266 0.82967 0.00424 0.85355 0.00530 0.87592 0.00587 0.89668 0.00599 0.91573 0.00574 0.93301 0.00517 0.94844 0.00439 0.96194 0.00346 0.97347 0.00246 0.98296 0.00146 0.99039 0.00049 0.99572 -0.00020 0.99893 -0.00082 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 73-K-170/22 (fx73k170-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx73k170-il | 50,000 | 9 | 5.2 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73k170-il | 50,000 | 5 | 13.3 at α=14.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73k170-il | 100,000 | 9 | 26.9 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73k170-il | 100,000 | 5 | 26.3 at α=11° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73k170-il | 200,000 | 9 | 63 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73k170-il | 200,000 | 5 | 65.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73k170-il | 500,000 | 9 | 112.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73k170-il | 500,000 | 5 | 110 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73k170-il | 1,000,000 | 9 | 145.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73k170-il | 1,000,000 | 5 | 138 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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