AH 63-K-127/24 (ah63k127-il)
AH 63-K-127/24 - Althaus AH 63-K-127/24 airfoil for use with flaps (K)
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(ah63k127-il) AH 63-K-127/24 Althaus AH 63-K-127/24 airfoil for use with flaps (K) Max thickness 12.7% at 40.2% chord. Max camber 3.8% at 43.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
AH 63-K-127/24 1.00000 0.00000 0.99893 0.00080 0.99572 0.00180 0.99039 0.00311 0.98296 0.00489 0.97347 0.00709 0.96194 0.00956 0.94844 0.01222 0.93301 0.01521 0.91573 0.01865 0.89668 0.02254 0.87592 0.02667 0.85355 0.03085 0.82967 0.03477 0.80438 0.03919 0.77779 0.04532 0.75000 0.05330 0.72114 0.06237 0.69134 0.07088 0.66072 0.07810 0.62941 0.08418 0.59755 0.08913 0.56526 0.09314 0.53270 0.09631 0.50000 0.09866 0.46730 0.10021 0.43474 0.10098 0.40245 0.10096 0.37059 0.10010 0.33928 0.09839 0.30866 0.09587 0.27886 0.09262 0.25000 0.08874 0.22221 0.08428 0.19562 0.07934 0.17033 0.07405 0.14645 0.06848 0.12408 0.06273 0.10332 0.05685 0.08427 0.05091 0.06699 0.04490 0.05156 0.03876 0.03806 0.03253 0.02653 0.02631 0.01704 0.02021 0.00961 0.01430 0.00428 0.00879 0.00107 0.00394 0.00000 0.00000 0.00107 -0.00310 0.00428 -0.00565 0.00961 -0.00795 0.01704 -0.01021 0.02653 -0.01245 0.03806 -0.01459 0.05156 -0.01655 0.06699 -0.01830 0.08427 -0.01986 0.10332 -0.02125 0.12408 -0.02246 0.14645 -0.02347 0.17033 -0.02426 0.19562 -0.02485 0.22221 -0.02527 0.25000 -0.02559 0.27886 -0.02585 0.30866 -0.02608 0.33928 -0.02626 0.37059 -0.02630 0.40245 -0.02611 0.43474 -0.02568 0.46730 -0.02508 0.50000 -0.02432 0.53270 -0.02335 0.56526 -0.02217 0.59755 -0.02087 0.62941 -0.01936 0.66072 -0.01756 0.69134 -0.01539 0.72114 -0.01298 0.75000 -0.01050 0.77779 -0.00795 0.80438 -0.00540 0.82967 -0.00292 0.85355 -0.00071 0.87592 0.00098 0.89668 0.00208 0.91573 0.00266 0.93301 0.00285 0.94844 0.00272 0.96194 0.00228 0.97347 0.00174 0.98296 0.00122 0.99039 0.00077 0.99572 0.00030 0.99893 0.00010 1.00000 0.00000 |
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Polars for AH 63-K-127/24 (ah63k127-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah63k127-il | 50,000 | 9 | 25.4 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah63k127-il | 50,000 | 5 | 23 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah63k127-il | 100,000 | 9 | 43.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah63k127-il | 100,000 | 5 | 44.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah63k127-il | 200,000 | 9 | 83.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah63k127-il | 200,000 | 5 | 81.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah63k127-il | 500,000 | 9 | 127.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah63k127-il | 500,000 | 5 | 115.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah63k127-il | 1,000,000 | 9 | 152.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah63k127-il | 1,000,000 | 5 | 137.8 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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