UAG 88-143/20 (uag8814320-il)
UAG 88-143/20 - UAG 88-143/20 airfoil
| Details | Dat file | Parser | |
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(uag8814320-il) UAG 88-143/20 UAG 88-143/20 airfoil Max thickness 14.3% at 43.5% chord. Max camber 6.2% at 46.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
UAG 88-143/20 1.00000 0.00002 0.99893 0.00053 0.99572 0.00196 0.99039 0.00403 0.98296 0.00660 0.97347 0.00967 0.96194 0.01327 0.94844 0.01742 0.93301 0.02218 0.91573 0.02756 0.89668 0.03360 0.87592 0.04036 0.85355 0.04794 0.82967 0.05651 0.80438 0.06628 0.77779 0.07682 0.75000 0.08719 0.72114 0.09659 0.69134 0.10480 0.66072 0.11193 0.62941 0.11801 0.59755 0.12305 0.56526 0.12706 0.53270 0.13006 0.50000 0.13208 0.46730 0.13318 0.43474 0.13338 0.40245 0.13272 0.37059 0.13122 0.33928 0.12892 0.30866 0.12584 0.27886 0.12201 0.25000 0.11747 0.22221 0.11226 0.19562 0.10642 0.17033 0.09998 0.14645 0.09301 0.12408 0.08557 0.10332 0.07774 0.08427 0.06961 0.06699 0.06128 0.05156 0.05288 0.03806 0.04454 0.02653 0.03633 0.01704 0.02829 0.00961 0.02053 0.00428 0.01343 0.00107 0.00789 0.00000 0.00000 0.00107 -0.00090 0.00428 -0.00398 0.00961 -0.00690 0.01704 -0.00956 0.02653 -0.01170 0.03806 -0.01312 0.05156 -0.01405 0.06699 -0.01467 0.08427 -0.01503 0.10332 -0.01518 0.12408 -0.01515 0.14645 -0.01494 0.17033 -0.01456 0.19562 -0.01405 0.22221 -0.01349 0.25000 -0.01294 0.27886 -0.01241 0.30866 -0.01188 0.33928 -0.01134 0.37059 -0.01080 0.40245 -0.01024 0.43474 -0.00968 0.46730 -0.00912 0.50000 -0.00855 0.53270 -0.00798 0.56526 -0.00741 0.59755 -0.00684 0.62941 -0.00628 0.66072 -0.00573 0.69134 -0.00519 0.72114 -0.00466 0.75000 -0.00415 0.77779 -0.00366 0.80438 -0.00319 0.82967 -0.00275 0.85355 -0.00233 0.87592 -0.00194 0.89668 -0.00157 0.91573 -0.00124 0.93301 -0.00094 0.94844 -0.00067 0.96194 -0.00044 0.97347 -0.00022 0.98296 -0.00004 0.99039 0.00006 0.99572 0.00009 0.99893 0.00008 1.00000 0.00002 |
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Polars for UAG 88-143/20 (uag8814320-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| uag8814320-il | 50,000 | 9 | 5.5 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| uag8814320-il | 50,000 | 5 | 15.3 at α=13.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| uag8814320-il | 100,000 | 9 | 32 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| uag8814320-il | 100,000 | 5 | 30.3 at α=11° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| uag8814320-il | 200,000 | 9 | 55.1 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| uag8814320-il | 200,000 | 5 | 53.2 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| uag8814320-il | 500,000 | 9 | 127 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| uag8814320-il | 500,000 | 5 | 123.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| uag8814320-il | 1,000,000 | 9 | 185.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| uag8814320-il | 1,000,000 | 5 | 169.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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