GOE 222 (MVA H.33) AIRFOIL (goe222-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 222 (MVA H.33) AIRFOIL (goe222-il) Reynolds number: 100,000 Max Cl/Cd: 47.49 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe222-il-100000-n5.txt Download as CSV file: xf-goe222-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 222 (MVA H.33) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.0742 0.10216 0.09660 -0.1196 0.9296 0.0522
-11.500 -0.0863 0.09316 0.08758 -0.1253 0.9260 0.0526
-11.250 -0.2070 0.06836 0.06253 -0.1401 0.9118 0.0513
-11.000 -0.2586 0.05923 0.05313 -0.1468 0.8981 0.0507
-10.750 -0.2865 0.05416 0.04786 -0.1499 0.8861 0.0507
-10.500 -0.2976 0.04970 0.04315 -0.1545 0.8772 0.0510
-10.250 -0.3058 0.04660 0.03982 -0.1571 0.8661 0.0515
-10.000 -0.2920 0.04334 0.03621 -0.1618 0.8616 0.0523
-9.750 -0.2864 0.04147 0.03411 -0.1622 0.8539 0.0528
-9.500 -0.2700 0.03954 0.03191 -0.1635 0.8489 0.0535
-9.250 -0.2449 0.03765 0.02972 -0.1658 0.8460 0.0543
-9.000 -0.2166 0.03607 0.02805 -0.1673 0.8441 0.0554
-8.750 -0.2105 0.03554 0.02755 -0.1647 0.8358 0.0563
-8.500 -0.1864 0.03451 0.02648 -0.1652 0.8325 0.0577
-8.250 -0.1585 0.03345 0.02534 -0.1663 0.8303 0.0591
-8.000 -0.1286 0.03246 0.02424 -0.1674 0.8285 0.0604
-7.750 -0.1178 0.03216 0.02389 -0.1654 0.8221 0.0613
-7.500 -0.0951 0.03158 0.02322 -0.1653 0.8180 0.0624
-7.250 -0.0670 0.03082 0.02249 -0.1661 0.8154 0.0642
-7.000 -0.0353 0.03000 0.02165 -0.1679 0.8136 0.0668
-6.750 -0.0010 0.02917 0.02073 -0.1702 0.8120 0.0697
-6.500 0.0103 0.02911 0.02060 -0.1686 0.8053 0.0715
-6.250 0.0389 0.02837 0.01985 -0.1702 0.8017 0.0745
-6.000 0.0733 0.02755 0.01894 -0.1727 0.7993 0.0792
-5.750 0.1128 0.02648 0.01783 -0.1760 0.7973 0.0893
-5.500 0.1578 0.02504 0.01639 -0.1805 0.7954 0.1176
-5.250 0.1774 0.02442 0.01598 -0.1805 0.7866 0.1609
-5.000 0.2169 0.02373 0.01549 -0.1829 0.7823 0.2274
-4.750 0.2588 0.02337 0.01505 -0.1851 0.7791 0.2649
-4.500 0.2790 0.02368 0.01528 -0.1839 0.7723 0.2814
-4.250 0.3068 0.02383 0.01529 -0.1840 0.7678 0.2964
-4.000 0.3409 0.02381 0.01510 -0.1851 0.7647 0.3112
-3.750 0.3767 0.02387 0.01509 -0.1862 0.7622 0.3243
-3.500 0.3995 0.02430 0.01552 -0.1852 0.7573 0.3357
-3.250 0.4212 0.02465 0.01577 -0.1843 0.7515 0.3477
-3.000 0.4519 0.02475 0.01587 -0.1844 0.7477 0.3568
-2.750 0.4899 0.02447 0.01541 -0.1863 0.7449 0.3661
-2.500 0.5174 0.02451 0.01544 -0.1862 0.7406 0.3714
-2.250 0.5355 0.02475 0.01562 -0.1848 0.7340 0.3764
-2.000 0.5695 0.02448 0.01515 -0.1862 0.7299 0.3825
-1.750 0.6065 0.02415 0.01477 -0.1877 0.7267 0.3864
-1.500 0.6297 0.02425 0.01485 -0.1870 0.7209 0.3905
-1.250 0.6519 0.02434 0.01488 -0.1862 0.7142 0.3951
-1.000 0.6882 0.02404 0.01439 -0.1878 0.7100 0.4004
-0.750 0.7271 0.02369 0.01399 -0.1897 0.7067 0.4044
-0.500 0.7353 0.02419 0.01457 -0.1865 0.6978 0.4078
-0.250 0.7661 0.02406 0.01438 -0.1871 0.6926 0.4128
0.000 0.8055 0.02373 0.01388 -0.1892 0.6888 0.4184
0.250 0.8142 0.02418 0.01441 -0.1860 0.6794 0.4212
0.500 0.8438 0.02405 0.01427 -0.1863 0.6735 0.4255
0.750 0.8716 0.02400 0.01419 -0.1863 0.6673 0.4308
1.000 0.8859 0.02430 0.01448 -0.1842 0.6579 0.4357
1.250 0.9212 0.02401 0.01415 -0.1854 0.6528 0.4407
1.500 0.9248 0.02455 0.01479 -0.1814 0.6419 0.4440
1.750 0.9573 0.02435 0.01454 -0.1822 0.6361 0.4496
2.000 0.9628 0.02491 0.01513 -0.1786 0.6252 0.4544
2.250 0.9934 0.02473 0.01494 -0.1790 0.6191 0.4602
2.500 1.0031 0.02532 0.01561 -0.1763 0.6082 0.4650
2.750 1.0349 0.02510 0.01533 -0.1768 0.6021 0.4721
3.000 1.0474 0.02569 0.01596 -0.1747 0.5912 0.4773
3.250 1.0778 0.02551 0.01577 -0.1750 0.5850 0.4838
3.500 1.0942 0.02602 0.01630 -0.1735 0.5755 0.4908
3.750 1.1259 0.02582 0.01605 -0.1740 0.5697 0.4989
4.000 1.1420 0.02635 0.01662 -0.1724 0.5605 0.5064
4.250 1.1723 0.02622 0.01642 -0.1727 0.5540 0.5158
4.500 1.1894 0.02673 0.01696 -0.1713 0.5452 0.5238
4.750 1.2174 0.02673 0.01690 -0.1713 0.5384 0.5346
5.000 1.2362 0.02719 0.01740 -0.1701 0.5304 0.5453
5.250 1.2602 0.02741 0.01761 -0.1696 0.5234 0.5575
5.500 1.2852 0.02764 0.01783 -0.1693 0.5174 0.5714
6.000 1.3299 0.02832 0.01856 -0.1680 0.5045 0.6036
6.250 1.3464 0.02889 0.01923 -0.1666 0.4975 0.6224
6.500 1.3650 0.02934 0.01977 -0.1655 0.4905 0.6466
6.750 1.3930 0.02933 0.01983 -0.1655 0.4849 0.6867
7.000 1.3916 0.02973 0.02070 -0.1609 0.4788 0.9430
7.250 1.4111 0.03034 0.02131 -0.1601 0.4734 1.0000
7.500 1.4393 0.03061 0.02148 -0.1603 0.4689 1.0000
7.750 1.4529 0.03152 0.02244 -0.1588 0.4634 1.0000
8.000 1.4660 0.03245 0.02341 -0.1572 0.4576 1.0000
8.250 1.4882 0.03292 0.02385 -0.1567 0.4524 1.0000
8.500 1.5054 0.03366 0.02461 -0.1556 0.4470 1.0000
8.750 1.5125 0.03490 0.02595 -0.1533 0.4409 1.0000
9.000 1.5301 0.03560 0.02665 -0.1523 0.4355 1.0000
9.250 1.5523 0.03609 0.02712 -0.1518 0.4306 1.0000
9.500 1.5524 0.03777 0.02897 -0.1490 0.4243 1.0000
9.750 1.5649 0.03876 0.03000 -0.1475 0.4185 1.0000
10.000 1.5881 0.03912 0.03033 -0.1470 0.4133 1.0000
10.250 1.5807 0.04136 0.03277 -0.1437 0.4061 1.0000
10.500 1.5910 0.04248 0.03393 -0.1421 0.3995 1.0000
10.750 1.5994 0.04376 0.03527 -0.1404 0.3930 1.0000
11.000 1.5951 0.04599 0.03765 -0.1378 0.3851 1.0000
11.250 1.6126 0.04659 0.03823 -0.1368 0.3790 1.0000
11.500 1.5990 0.04978 0.04164 -0.1338 0.3704 1.0000
11.750 1.6082 0.05107 0.04295 -0.1324 0.3632 1.0000
12.000 1.5981 0.05423 0.04628 -0.1301 0.3541 1.0000
12.250 1.6055 0.05574 0.04781 -0.1288 0.3465 1.0000
12.500 1.5937 0.05935 0.05158 -0.1267 0.3367 1.0000
12.750 1.6044 0.06058 0.05281 -0.1256 0.3296 1.0000
13.000 1.5905 0.06465 0.05705 -0.1239 0.3197 1.0000
13.250 1.5980 0.06632 0.05872 -0.1228 0.3127 1.0000
13.500 1.5896 0.06995 0.06248 -0.1215 0.3042 1.0000
13.750 1.6006 0.07125 0.06375 -0.1206 0.2982 1.0000
14.000 1.5916 0.07512 0.06776 -0.1195 0.2906 1.0000
14.250 1.6016 0.07655 0.06919 -0.1187 0.2851 1.0000
14.500 1.5993 0.07964 0.07236 -0.1178 0.2790 1.0000
14.750 1.5995 0.08243 0.07522 -0.1171 0.2730 1.0000
15.000 1.6153 0.08306 0.07578 -0.1164 0.2677 1.0000
15.250 1.6037 0.08754 0.08043 -0.1158 0.2617 1.0000
15.500 1.6078 0.08981 0.08272 -0.1152 0.2556 1.0000
15.750 1.6128 0.09194 0.08486 -0.1147 0.2498 1.0000
16.000 1.6030 0.09627 0.08934 -0.1145 0.2438 1.0000
16.250 1.6147 0.09740 0.09041 -0.1140 0.2375 1.0000
16.500 1.6068 0.10156 0.09470 -0.1140 0.2321 1.0000
16.750 1.5989 0.10578 0.09906 -0.1142 0.2265 1.0000
17.000 1.6139 0.10636 0.09954 -0.1137 0.2205 1.0000
17.250 1.6002 0.11160 0.10499 -0.1144 0.2156 1.0000
17.500 1.5899 0.11634 0.10989 -0.1152 0.2103 1.0000
17.750 1.6008 0.11757 0.11108 -0.1150 0.2046 1.0000
18.000 1.5884 0.12278 0.11648 -0.1162 0.1999 1.0000
18.250 1.5738 0.12844 0.12233 -0.1178 0.1949 1.0000
18.500 1.5788 0.13075 0.12465 -0.1183 0.1890 1.0000
18.750 1.5640 0.13658 0.13066 -0.1202 0.1841 1.0000
19.000 1.5446 0.14337 0.13765 -0.1229 0.1789 1.0000
19.250 1.5516 0.14539 0.13966 -0.1235 0.1724 1.0000
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Polar data table (+)
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