AH 80-129 (ah80129-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 80-129 (ah80129-il) Reynolds number: 1,000,000 Max Cl/Cd: 143.72 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah80129-il-1000000-n5.txt Download as CSV file: xf-ah80129-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 80-129
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2526 0.08812 0.08551 -0.0686 0.7511 0.0036
-9.750 -0.2599 0.08110 0.07853 -0.0727 0.7495 0.0034
-9.500 -0.2448 0.08000 0.07742 -0.0744 0.7476 0.0044
-9.250 -0.2703 0.06824 0.06572 -0.0828 0.7458 0.0032
-9.000 -0.2622 0.06499 0.06248 -0.0873 0.7435 0.0034
-8.750 -0.3067 0.05156 0.04895 -0.0978 0.7407 0.0032
-8.500 -0.3161 0.04595 0.04319 -0.0985 0.7384 0.0032
-8.250 -0.3233 0.04057 0.03765 -0.0974 0.7364 0.0033
-8.000 -0.3635 0.02805 0.02458 -0.0911 0.7337 0.0035
-7.750 -0.3735 0.02229 0.01821 -0.0861 0.7314 0.0035
-7.500 -0.3213 0.02744 0.02382 -0.0902 0.7293 0.0041
-7.250 -0.3301 0.02147 0.01720 -0.0848 0.7271 0.0040
-7.000 -0.3149 0.01980 0.01527 -0.0830 0.7252 0.0041
-6.750 -0.2952 0.01880 0.01412 -0.0819 0.7232 0.0044
-6.500 -0.2753 0.01769 0.01282 -0.0806 0.7210 0.0047
-6.250 -0.2579 0.01590 0.01074 -0.0789 0.7186 0.0046
-6.000 -0.2366 0.01486 0.00951 -0.0778 0.7161 0.0047
-5.750 -0.2141 0.01402 0.00851 -0.0769 0.7139 0.0050
-5.500 -0.1921 0.01307 0.00738 -0.0758 0.7117 0.0050
-5.250 -0.1677 0.01257 0.00680 -0.0753 0.7096 0.0051
-5.000 -0.1447 0.01179 0.00588 -0.0744 0.7071 0.0051
-4.750 -0.1217 0.01114 0.00512 -0.0735 0.7045 0.0052
-4.500 -0.0979 0.01067 0.00456 -0.0728 0.7019 0.0053
-4.250 -0.0742 0.01024 0.00404 -0.0720 0.6997 0.0054
-4.000 -0.0498 0.00992 0.00365 -0.0714 0.6972 0.0056
-3.750 -0.0251 0.00959 0.00327 -0.0709 0.6950 0.0056
-3.500 -0.0017 0.00914 0.00272 -0.0700 0.6924 0.0069
-3.250 0.0241 0.00898 0.00251 -0.0697 0.6896 0.0066
-3.000 0.0492 0.00877 0.00226 -0.0693 0.6867 0.0079
-2.750 0.0749 0.00863 0.00209 -0.0690 0.6840 0.0086
-2.500 0.1012 0.00850 0.00193 -0.0687 0.6813 0.0086
-2.250 0.1272 0.00836 0.00177 -0.0685 0.6785 0.0108
-2.000 0.1523 0.00816 0.00163 -0.0681 0.6755 0.0273
-1.750 0.1768 0.00794 0.00153 -0.0675 0.6727 0.0615
-1.500 0.2023 0.00782 0.00144 -0.0672 0.6697 0.0814
-1.250 0.2275 0.00763 0.00137 -0.0669 0.6668 0.1194
-1.000 0.2495 0.00726 0.00130 -0.0660 0.6633 0.2206
-0.750 0.2705 0.00687 0.00123 -0.0649 0.6600 0.3355
-0.500 0.2934 0.00665 0.00119 -0.0641 0.6570 0.4083
-0.250 0.3156 0.00637 0.00116 -0.0632 0.6536 0.4943
0.000 0.3304 0.00584 0.00113 -0.0606 0.6499 0.6556
0.250 0.3451 0.00549 0.00115 -0.0578 0.6464 0.7793
0.500 0.3673 0.00535 0.00120 -0.0566 0.6430 0.8498
0.750 0.3966 0.00529 0.00124 -0.0570 0.6391 0.8889
1.000 0.4286 0.00529 0.00128 -0.0580 0.6354 0.9098
1.500 0.5007 0.00536 0.00136 -0.0621 0.6282 0.9415
1.750 0.5426 0.00541 0.00141 -0.0655 0.6238 0.9500
2.000 0.5737 0.00547 0.00145 -0.0664 0.6188 0.9559
2.250 0.6101 0.00553 0.00149 -0.0686 0.6135 0.9578
2.500 0.6443 0.00558 0.00154 -0.0704 0.6084 0.9598
2.750 0.6766 0.00566 0.00160 -0.0716 0.6036 0.9624
3.000 0.7071 0.00572 0.00167 -0.0725 0.5992 0.9657
3.250 0.7359 0.00578 0.00174 -0.0730 0.5946 0.9693
3.500 0.7685 0.00588 0.00182 -0.0744 0.5886 0.9709
3.750 0.8004 0.00596 0.00191 -0.0756 0.5826 0.9727
4.000 0.8310 0.00606 0.00201 -0.0766 0.5765 0.9751
4.250 0.8609 0.00615 0.00214 -0.0773 0.5709 0.9779
4.500 0.8885 0.00626 0.00225 -0.0776 0.5642 0.9815
4.750 0.9198 0.00640 0.00239 -0.0788 0.5526 0.9828
5.000 0.9486 0.00670 0.00259 -0.0795 0.5241 0.9849
5.250 0.9729 0.00725 0.00294 -0.0795 0.4746 0.9887
5.500 0.9771 0.00984 0.00439 -0.0773 0.2667 0.9967
5.750 0.9798 0.01118 0.00528 -0.0737 0.1779 1.0000
6.000 0.9592 0.01243 0.00614 -0.0651 0.1004 1.0000
6.250 0.9696 0.01280 0.00650 -0.0622 0.0917 1.0000
6.500 0.9750 0.01356 0.00716 -0.0590 0.0659 1.0000
6.750 0.9761 0.01480 0.00820 -0.0556 0.0226 1.0000
7.000 0.9888 0.01558 0.00893 -0.0540 0.0105 1.0000
7.250 1.0024 0.01636 0.00967 -0.0525 0.0042 1.0000
7.500 1.0178 0.01706 0.01042 -0.0513 0.0029 1.0000
7.750 1.0323 0.01784 0.01127 -0.0500 0.0028 1.0000
8.000 1.0500 0.01843 0.01187 -0.0492 0.0027 1.0000
8.250 1.0666 0.01909 0.01255 -0.0483 0.0025 1.0000
8.500 1.0810 0.01992 0.01343 -0.0472 0.0024 1.0000
8.750 1.0927 0.02095 0.01455 -0.0457 0.0024 1.0000
9.000 1.1053 0.02193 0.01558 -0.0444 0.0024 1.0000
9.250 1.1181 0.02291 0.01661 -0.0432 0.0022 1.0000
9.500 1.1313 0.02386 0.01761 -0.0421 0.0021 1.0000
9.750 1.1435 0.02490 0.01873 -0.0409 0.0021 1.0000
10.000 1.1552 0.02597 0.01986 -0.0398 0.0021 1.0000
10.250 1.1649 0.02722 0.02117 -0.0384 0.0020 1.0000
10.500 1.1796 0.02809 0.02203 -0.0377 0.0014 1.0000
10.750 1.1804 0.03007 0.02413 -0.0355 0.0011 1.0000
11.000 1.1850 0.03177 0.02592 -0.0339 0.0012 1.0000
11.250 1.1958 0.03302 0.02723 -0.0329 0.0012 1.0000
11.500 1.2027 0.03463 0.02891 -0.0316 0.0013 1.0000
11.750 1.2011 0.03701 0.03143 -0.0296 0.0012 1.0000
12.000 1.2065 0.03882 0.03333 -0.0283 0.0012 1.0000
12.250 1.2119 0.04068 0.03528 -0.0270 0.0012 1.0000
12.500 1.2232 0.04206 0.03673 -0.0264 0.0011 1.0000
12.750 1.2258 0.04425 0.03905 -0.0249 0.0010 1.0000
13.000 1.2363 0.04571 0.04057 -0.0244 0.0011 1.0000
13.250 1.2434 0.04754 0.04251 -0.0236 0.0011 1.0000
13.500 1.2450 0.04993 0.04504 -0.0222 0.0011 1.0000
13.750 1.2474 0.05231 0.04755 -0.0210 0.0011 1.0000
14.000 1.2548 0.05423 0.04956 -0.0206 0.0011 1.0000
14.250 1.2579 0.05667 0.05213 -0.0198 0.0011 1.0000
14.500 1.2577 0.05946 0.05506 -0.0190 0.0011 1.0000
14.750 1.2544 0.06279 0.05859 -0.0179 0.0011 1.0000
15.000 1.2474 0.06669 0.06271 -0.0169 0.0010 1.0000
15.250 1.2477 0.06968 0.06581 -0.0170 0.0011 1.0000
15.500 1.2392 0.07401 0.07033 -0.0167 0.0011 1.0000
15.750 1.2361 0.07770 0.07415 -0.0171 0.0011 1.0000
16.000 1.2185 0.08363 0.08034 -0.0173 0.0010 1.0000
16.250 1.1987 0.09020 0.08714 -0.0182 0.0010 1.0000
16.500 1.1888 0.09542 0.09249 -0.0197 0.0010 1.0000
16.750 1.1592 0.10434 0.10169 -0.0220 0.0010 1.0000
17.000 1.1560 0.10879 0.10621 -0.0239 0.0011 1.0000
17.250 1.1299 0.11777 0.11540 -0.0274 0.0011 1.0000
17.500 1.1024 0.12780 0.12564 -0.0318 0.0011 1.0000
17.750 1.0918 0.13454 0.13249 -0.0354 0.0011 1.0000
18.000 1.0817 0.14153 0.13957 -0.0392 0.0011 1.0000
18.250 1.0572 0.15256 0.15076 -0.0452 0.0011 1.0000
18.500 1.0358 0.16377 0.16210 -0.0514 0.0012 1.0000
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Polar data table (+)
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