AH 79-100 C AIRFOIL (ah79100c-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 79-100 C AIRFOIL (ah79100c-il) Reynolds number: 100,000 Max Cl/Cd: 61.75 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah79100c-il-100000.txt Download as CSV file: xf-ah79100c-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: AH 79-100 C AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.500 -0.3313 0.11531 0.11119 -0.0298 0.9792 0.0691
-6.250 -0.3372 0.11439 0.11031 -0.0325 0.9722 0.0707
-6.000 -0.3304 0.11299 0.10893 -0.0438 0.9654 0.0717
-5.750 -0.3231 0.10903 0.10500 -0.0484 0.9587 0.0723
-5.500 -0.3129 0.10426 0.10022 -0.0412 0.9559 0.0740
-5.250 -0.2981 0.10106 0.09702 -0.0415 0.9518 0.0766
-5.000 -0.2923 0.09842 0.09439 -0.0428 0.9458 0.0791
-4.750 -0.2510 0.09430 0.09013 -0.0659 0.9382 0.0858
-4.500 -0.2474 0.09001 0.08590 -0.0638 0.9338 0.0870
-4.250 -0.2400 0.08747 0.08339 -0.0583 0.9302 0.0901
-4.000 -0.1884 0.08203 0.07773 -0.0787 0.9236 0.1013
-3.750 -0.1881 0.07947 0.07527 -0.0725 0.9193 0.1033
-3.500 -0.1503 0.07584 0.07154 -0.0791 0.9156 0.1132
-3.250 -0.0876 0.07114 0.06641 -0.0976 0.9092 0.1306
-3.000 -0.0860 0.06790 0.06340 -0.0922 0.9051 0.1335
-2.750 -0.0168 0.06366 0.05877 -0.1069 0.9019 0.1628
-2.500 -0.0157 0.06166 0.05693 -0.1022 0.8957 0.1663
-2.250 0.0329 0.05857 0.05361 -0.1103 0.8912 0.1960
-1.750 0.2297 0.04159 0.03393 -0.1444 0.8894 0.0988
-1.500 0.2825 0.03979 0.03149 -0.1493 0.8871 0.1015
-1.250 0.3021 0.03902 0.03054 -0.1487 0.8799 0.1030
-1.000 0.3408 0.03817 0.02948 -0.1508 0.8757 0.1075
-0.750 0.3864 0.03739 0.02853 -0.1540 0.8728 0.1198
-0.500 0.4030 0.03747 0.02850 -0.1526 0.8647 0.1300
-0.250 0.4405 0.03699 0.02815 -0.1545 0.8604 0.1550
0.000 0.4862 0.03641 0.02771 -0.1576 0.8577 0.2101
0.250 0.5010 0.03646 0.02815 -0.1562 0.8487 0.2879
0.500 0.5391 0.03516 0.02830 -0.1578 0.8453 0.6942
0.750 0.5516 0.03513 0.02838 -0.1549 0.8370 1.0000
1.000 0.5856 0.03544 0.02839 -0.1561 0.8311 1.0000
1.250 0.6312 0.03545 0.02815 -0.1589 0.8279 1.0000
1.500 0.6419 0.03632 0.02891 -0.1568 0.8172 1.0000
1.750 0.6858 0.03625 0.02867 -0.1593 0.8136 1.0000
2.000 0.6981 0.03715 0.02951 -0.1574 0.8030 1.0000
2.250 0.7410 0.03700 0.02923 -0.1597 0.7991 1.0000
2.500 0.7561 0.03782 0.03000 -0.1581 0.7884 1.0000
2.750 0.7994 0.03748 0.02958 -0.1602 0.7842 1.0000
3.000 0.8155 0.03827 0.03034 -0.1588 0.7735 1.0000
3.250 0.8579 0.03787 0.02990 -0.1607 0.7694 1.0000
3.500 0.8743 0.03865 0.03068 -0.1593 0.7586 1.0000
3.750 0.9171 0.03810 0.03011 -0.1611 0.7545 1.0000
4.000 0.9646 0.03721 0.02925 -0.1634 0.7518 1.0000
4.250 0.9797 0.03787 0.02992 -0.1616 0.7395 1.0000
4.500 1.0311 0.03649 0.02858 -0.1641 0.7374 1.0000
4.750 1.0445 0.03724 0.02940 -0.1621 0.7246 1.0000
5.000 1.0961 0.03566 0.02788 -0.1645 0.7228 1.0000
5.250 1.1525 0.03372 0.02601 -0.1676 0.7215 1.0000
5.500 1.1665 0.03420 0.02660 -0.1652 0.7086 1.0000
5.750 1.2291 0.03186 0.02437 -0.1691 0.7069 1.0000
6.250 1.2807 0.03130 0.02404 -0.1672 0.6852 1.0000
6.500 1.3407 0.02917 0.02206 -0.1709 0.6789 1.0000
6.750 1.3710 0.02865 0.02168 -0.1706 0.6670 1.0000
7.000 1.4230 0.02729 0.02047 -0.1736 0.6571 1.0000
7.250 1.4696 0.02620 0.01951 -0.1759 0.6439 1.0000
7.500 1.4912 0.02596 0.01940 -0.1740 0.6269 1.0000
7.750 1.5118 0.02576 0.01929 -0.1719 0.6082 1.0000
8.000 1.5376 0.02546 0.01907 -0.1708 0.5884 1.0000
8.250 1.5608 0.02531 0.01899 -0.1692 0.5667 1.0000
8.500 1.5727 0.02547 0.01916 -0.1657 0.5418 1.0000
8.750 1.5787 0.02577 0.01940 -0.1613 0.5123 1.0000
9.000 1.5809 0.02627 0.01974 -0.1563 0.4786 1.0000
9.250 1.5772 0.02722 0.02055 -0.1509 0.4444 1.0000
9.500 1.5729 0.02843 0.02163 -0.1457 0.4109 1.0000
9.750 1.5704 0.02978 0.02289 -0.1411 0.3802 1.0000
10.000 1.5685 0.03127 0.02431 -0.1369 0.3513 1.0000
10.250 1.5655 0.03295 0.02592 -0.1329 0.3228 1.0000
10.500 1.5606 0.03488 0.02778 -0.1289 0.2925 1.0000
10.750 1.5532 0.03715 0.02995 -0.1250 0.2581 1.0000
11.000 1.5411 0.04000 0.03261 -0.1210 0.2156 1.0000
11.250 1.5210 0.04391 0.03610 -0.1169 0.1559 1.0000
11.500 1.4975 0.04868 0.04030 -0.1131 0.0993 1.0000
11.750 1.4807 0.05317 0.04451 -0.1101 0.0747 1.0000
12.000 1.4711 0.05705 0.04838 -0.1078 0.0645 1.0000
12.250 1.4623 0.06095 0.05228 -0.1059 0.0594 1.0000
12.500 1.4606 0.06419 0.05567 -0.1043 0.0551 1.0000
12.750 1.4586 0.06750 0.05906 -0.1029 0.0520 1.0000
13.000 1.4591 0.07061 0.06212 -0.1013 0.0496 1.0000
13.250 1.4696 0.07271 0.06438 -0.0999 0.0475 1.0000
13.500 1.4836 0.07455 0.06632 -0.0986 0.0453 1.0000
13.750 1.4984 0.07640 0.06821 -0.0974 0.0431 1.0000
14.000 1.5352 0.07737 0.06908 -0.0963 0.0403 1.0000
14.250 1.5526 0.07976 0.07176 -0.0953 0.0396 1.0000
14.500 1.5678 0.08266 0.07497 -0.0943 0.0392 1.0000
14.750 1.5757 0.08621 0.07886 -0.0934 0.0390 1.0000
15.000 1.5767 0.09027 0.08326 -0.0926 0.0389 1.0000
15.250 1.5721 0.09474 0.08806 -0.0920 0.0390 1.0000
15.500 1.5639 0.09953 0.09319 -0.0917 0.0391 1.0000
15.750 1.5525 0.10466 0.09863 -0.0918 0.0393 1.0000
16.000 1.5393 0.11008 0.10434 -0.0924 0.0395 1.0000
16.250 1.5248 0.11578 0.11031 -0.0936 0.0397 1.0000
16.500 1.5100 0.12178 0.11655 -0.0952 0.0400 1.0000
16.750 1.4949 0.12813 0.12312 -0.0973 0.0403 1.0000
17.000 1.4821 0.13446 0.12968 -0.0998 0.0406 1.0000
17.250 1.4602 0.14105 0.13653 -0.1037 0.0409 1.0000
17.500 1.4298 0.15006 0.14585 -0.1100 0.0415 1.0000
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Polar data table (+)
Polar graphs
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