GOE 122 (MVA H.2) AIRFOIL (goe122-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 122 (MVA H.2) AIRFOIL (goe122-il) Reynolds number: 50,000 Max Cl/Cd: 37.59 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe122-il-50000.txt Download as CSV file: xf-goe122-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 122 (MVA H.2) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4544 0.11841 0.11180 -0.0044 1.0000 0.1348
-8.500 -0.4286 0.11070 0.10405 -0.0008 1.0000 0.1438
-8.250 -0.4338 0.10956 0.10302 -0.0043 1.0000 0.1488
-8.000 -0.4216 0.10460 0.09809 -0.0038 1.0000 0.1539
-7.750 -0.4175 0.10189 0.09544 -0.0051 1.0000 0.1619
-7.500 -0.4209 0.09995 0.09363 -0.0099 1.0000 0.1657
-7.250 -0.4065 0.09548 0.08914 -0.0077 1.0000 0.1763
-6.750 -0.3976 0.09052 0.08430 -0.0164 1.0000 0.1943
-6.500 -0.3846 0.08589 0.07974 -0.0131 1.0000 0.2069
-6.250 -0.3756 0.08250 0.07640 -0.0135 1.0000 0.2208
-6.000 -0.3680 0.07970 0.07366 -0.0157 1.0000 0.2376
-5.750 -0.3605 0.07683 0.07085 -0.0179 1.0000 0.2549
-5.500 -0.3505 0.07302 0.06711 -0.0150 1.0000 0.2725
-5.250 -0.3421 0.07012 0.06428 -0.0140 1.0000 0.2945
-5.000 -0.3358 0.06714 0.06136 -0.0129 1.0000 0.3177
-4.750 -0.3311 0.06446 0.05878 -0.0108 1.0000 0.3465
-4.500 -0.3275 0.06182 0.05624 -0.0069 1.0000 0.3791
-4.250 -0.0197 0.03956 0.03309 -0.0099 1.0000 0.9965
-4.000 -0.0745 0.04187 0.03565 0.0038 1.0000 0.9565
-3.750 -0.0451 0.03876 0.03253 -0.0011 1.0000 0.9694
-3.500 -0.0758 0.03896 0.03293 0.0063 1.0000 0.9331
-3.250 -0.1147 0.03943 0.03363 0.0143 1.0000 0.8976
-3.000 -0.1512 0.03941 0.03389 0.0209 1.0000 0.8638
-2.750 -0.1961 0.03947 0.03424 0.0294 1.0000 0.8397
-2.500 -0.2578 0.04004 0.03510 0.0414 1.0000 0.8234
-2.250 -0.0878 0.03562 0.02768 -0.0438 1.0000 0.2247
-2.000 -0.0554 0.03303 0.02459 -0.0454 1.0000 0.1910
-1.750 -0.0256 0.03115 0.02223 -0.0463 1.0000 0.1730
-1.500 0.0035 0.02980 0.02033 -0.0470 1.0000 0.1616
-1.250 0.0297 0.02874 0.01899 -0.0476 1.0000 0.1595
-1.000 0.0547 0.02800 0.01798 -0.0480 1.0000 0.1593
-0.750 0.0786 0.02745 0.01720 -0.0483 1.0000 0.1574
-0.500 0.1356 0.02660 0.01597 -0.0539 0.9869 0.1568
-0.250 0.2020 0.02591 0.01497 -0.0608 0.9705 0.1626
0.000 0.2598 0.02529 0.01436 -0.0665 0.9504 0.1809
0.250 0.3188 0.02457 0.01387 -0.0723 0.9306 0.2171
0.500 0.3784 0.02226 0.01322 -0.0769 0.9133 1.0000
0.750 0.4256 0.02264 0.01313 -0.0800 0.8898 1.0000
1.000 0.4725 0.02289 0.01311 -0.0828 0.8690 1.0000
1.250 0.5052 0.02331 0.01337 -0.0833 0.8454 1.0000
1.500 0.5399 0.02359 0.01352 -0.0837 0.8256 1.0000
1.750 0.5681 0.02402 0.01384 -0.0832 0.8053 1.0000
2.000 0.5949 0.02448 0.01422 -0.0826 0.7861 1.0000
2.250 0.6221 0.02490 0.01458 -0.0819 0.7690 1.0000
2.500 0.6486 0.02534 0.01499 -0.0811 0.7530 1.0000
2.750 0.6742 0.02586 0.01547 -0.0802 0.7377 1.0000
3.000 0.6993 0.02644 0.01604 -0.0794 0.7229 1.0000
3.250 0.7240 0.02700 0.01661 -0.0785 0.7081 1.0000
3.500 0.7486 0.02750 0.01714 -0.0773 0.6931 1.0000
3.750 0.7736 0.02774 0.01737 -0.0756 0.6771 1.0000
4.000 0.7962 0.02819 0.01785 -0.0740 0.6586 1.0000
4.250 0.8193 0.02859 0.01828 -0.0724 0.6404 1.0000
4.500 0.8430 0.02909 0.01887 -0.0710 0.6244 1.0000
4.750 0.8667 0.02977 0.01964 -0.0700 0.6094 1.0000
5.000 0.8901 0.03050 0.02046 -0.0689 0.5942 1.0000
5.250 0.9134 0.03125 0.02133 -0.0678 0.5788 1.0000
5.500 0.9368 0.03196 0.02220 -0.0665 0.5629 1.0000
5.750 0.9605 0.03263 0.02299 -0.0652 0.5467 1.0000
6.000 0.9843 0.03333 0.02382 -0.0639 0.5306 1.0000
6.250 1.0085 0.03380 0.02439 -0.0623 0.5131 1.0000
6.500 1.0305 0.03378 0.02451 -0.0600 0.4887 1.0000
6.750 1.0541 0.03334 0.02410 -0.0576 0.4643 1.0000
7.000 1.0790 0.03311 0.02392 -0.0555 0.4432 1.0000
7.250 1.1014 0.03333 0.02428 -0.0538 0.4222 1.0000
7.500 1.1259 0.03245 0.02340 -0.0514 0.3963 1.0000
7.750 1.1443 0.03184 0.02297 -0.0489 0.3643 1.0000
8.000 1.1594 0.03092 0.02216 -0.0458 0.3216 1.0000
8.250 1.1633 0.03095 0.02208 -0.0419 0.2457 1.0000
8.500 1.1629 0.03348 0.02371 -0.0387 0.1812 1.0000
8.750 1.1727 0.03634 0.02626 -0.0364 0.1527 1.0000
9.000 1.1870 0.03873 0.02868 -0.0346 0.1345 1.0000
9.250 1.2039 0.04103 0.03100 -0.0330 0.1222 1.0000
9.500 1.2260 0.04346 0.03332 -0.0318 0.1137 1.0000
9.750 1.2424 0.04608 0.03632 -0.0304 0.1064 1.0000
10.000 1.2627 0.04901 0.03926 -0.0294 0.1008 1.0000
10.250 1.2758 0.05282 0.04363 -0.0280 0.0986 1.0000
10.500 1.2828 0.05680 0.04807 -0.0264 0.0966 1.0000
10.750 1.2855 0.06070 0.05233 -0.0249 0.0946 1.0000
11.000 1.2923 0.06433 0.05612 -0.0237 0.0919 1.0000
11.250 1.2959 0.06884 0.06081 -0.0226 0.0904 1.0000
11.500 1.2767 0.07316 0.06555 -0.0208 0.0909 1.0000
11.750 1.2121 0.07975 0.07271 -0.0209 0.0953 1.0000
12.000 1.1766 0.08720 0.08039 -0.0239 0.0979 1.0000
12.250 1.1476 0.09519 0.08850 -0.0280 0.0998 1.0000
12.500 1.1244 0.10339 0.09672 -0.0322 0.1012 1.0000
12.750 0.9999 0.13851 0.13157 -0.0595 0.1218 1.0000
13.000 0.9919 0.14619 0.13921 -0.0629 0.1241 1.0000
13.250 0.9897 0.15271 0.14571 -0.0653 0.1255 1.0000
13.500 0.9937 0.15835 0.15136 -0.0665 0.1268 1.0000
13.750 0.7162 0.16352 0.15669 -0.0593 0.2507 1.0000
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Polar data table (+)
Polar graphs
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