GOE 226 (MVA H.36) AIRFOIL (goe226-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 226 (MVA H.36) AIRFOIL (goe226-il) Reynolds number: 200,000 Max Cl/Cd: 85.48 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe226-il-200000.txt Download as CSV file: xf-goe226-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 226 (MVA H.36) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 0.0539 0.09606 0.09219 -0.1048 0.9158 0.0728
-9.000 0.0452 0.09458 0.09071 -0.1091 0.9059 0.0765
-8.750 0.0445 0.09139 0.08752 -0.1113 0.8971 0.0773
-8.500 0.0640 0.08862 0.08473 -0.1087 0.8914 0.0782
-8.250 0.0774 0.08647 0.08253 -0.1075 0.8861 0.0795
-8.000 0.0877 0.08446 0.08053 -0.1078 0.8772 0.0812
-7.750 0.0951 0.08229 0.07832 -0.1084 0.8703 0.0836
-7.500 0.0782 0.07981 0.07588 -0.1204 0.8569 0.0873
-7.250 0.0923 0.07674 0.07277 -0.1160 0.8529 0.0880
-7.000 0.1091 0.07479 0.07080 -0.1135 0.8478 0.0891
-6.750 0.1239 0.07303 0.06904 -0.1129 0.8409 0.0909
-6.500 0.1371 0.07093 0.06691 -0.1140 0.8355 0.0935
-6.250 0.1520 0.06529 0.06124 -0.1327 0.8261 0.0995
-6.000 0.1648 0.06334 0.05927 -0.1294 0.8207 0.1003
-5.750 0.2458 0.02904 0.02335 -0.1915 0.8161 0.0769
-5.500 0.2758 0.02621 0.02029 -0.1946 0.8092 0.0781
-5.250 0.3034 0.02556 0.01967 -0.1949 0.8038 0.0801
-5.000 0.3365 0.02409 0.01793 -0.1967 0.8000 0.0824
-4.750 0.3694 0.02247 0.01593 -0.1987 0.7948 0.0845
-4.500 0.4012 0.02138 0.01444 -0.2000 0.7888 0.0868
-4.250 0.4317 0.02025 0.01323 -0.2009 0.7845 0.0899
-4.000 0.4630 0.01964 0.01249 -0.2015 0.7807 0.0935
-3.750 0.4912 0.01914 0.01184 -0.2017 0.7736 0.0971
-3.500 0.5219 0.01831 0.01086 -0.2023 0.7686 0.1012
-3.250 0.5528 0.01781 0.01031 -0.2027 0.7648 0.1065
-3.000 0.5812 0.01756 0.00993 -0.2028 0.7586 0.1118
-2.750 0.6106 0.01690 0.00931 -0.2032 0.7530 0.1186
-2.500 0.6416 0.01656 0.00881 -0.2035 0.7487 0.1269
-2.250 0.6705 0.01609 0.00844 -0.2038 0.7434 0.1370
-2.000 0.6993 0.01579 0.00816 -0.2040 0.7374 0.1489
-1.750 0.7297 0.01548 0.00782 -0.2043 0.7326 0.1627
-1.500 0.7591 0.01532 0.00765 -0.2044 0.7274 0.1777
-1.250 0.7872 0.01522 0.00760 -0.2044 0.7207 0.1942
-1.000 0.8173 0.01502 0.00743 -0.2046 0.7153 0.2153
-0.750 0.8457 0.01497 0.00741 -0.2046 0.7089 0.2452
-0.500 0.8740 0.01493 0.00743 -0.2045 0.7016 0.2816
-0.250 0.9040 0.01488 0.00735 -0.2046 0.6959 0.3137
0.000 0.9301 0.01497 0.00748 -0.2042 0.6875 0.3376
0.250 0.9591 0.01494 0.00741 -0.2041 0.6808 0.3580
0.500 0.9860 0.01501 0.00749 -0.2038 0.6725 0.3755
0.750 1.0140 0.01499 0.00745 -0.2036 0.6645 0.3913
1.000 1.0408 0.01504 0.00752 -0.2032 0.6554 0.4064
1.250 1.0687 0.01505 0.00748 -0.2030 0.6463 0.4226
1.500 1.0944 0.01513 0.00759 -0.2025 0.6353 0.4401
1.750 1.1220 0.01519 0.00758 -0.2022 0.6256 0.4582
2.000 1.1472 0.01526 0.00769 -0.2016 0.6137 0.4764
2.250 1.1729 0.01537 0.00780 -0.2011 0.6019 0.4973
2.500 1.1997 0.01547 0.00784 -0.2007 0.5912 0.5206
2.750 1.2239 0.01556 0.00802 -0.2000 0.5786 0.5451
3.000 1.2488 0.01570 0.00820 -0.1995 0.5672 0.5742
3.250 1.2748 0.01582 0.00829 -0.1990 0.5576 0.6068
3.500 1.2984 0.01593 0.00851 -0.1982 0.5456 0.6449
3.750 1.3222 0.01600 0.00863 -0.1974 0.5352 0.6966
4.000 1.3420 0.01570 0.00860 -0.1957 0.5260 1.0000
4.250 1.3670 0.01601 0.00883 -0.1953 0.5167 1.0000
4.500 1.3924 0.01632 0.00900 -0.1949 0.5094 1.0000
4.750 1.4169 0.01666 0.00931 -0.1944 0.5020 1.0000
5.000 1.4416 0.01700 0.00957 -0.1939 0.4952 1.0000
5.250 1.4670 0.01739 0.00985 -0.1936 0.4895 1.0000
5.500 1.4908 0.01776 0.01024 -0.1930 0.4834 1.0000
5.750 1.5159 0.01815 0.01056 -0.1926 0.4779 1.0000
6.000 1.5414 0.01859 0.01093 -0.1923 0.4728 1.0000
6.250 1.5642 0.01901 0.01138 -0.1916 0.4671 1.0000
6.500 1.5887 0.01943 0.01177 -0.1911 0.4616 1.0000
6.750 1.6148 0.01992 0.01219 -0.1910 0.4566 1.0000
7.000 1.6361 0.02038 0.01273 -0.1900 0.4512 1.0000
7.250 1.6597 0.02085 0.01320 -0.1894 0.4461 1.0000
7.500 1.6883 0.02139 0.01362 -0.1898 0.4414 1.0000
7.750 1.7075 0.02190 0.01427 -0.1885 0.4365 1.0000
8.000 1.7284 0.02240 0.01483 -0.1875 0.4310 1.0000
8.250 1.7543 0.02293 0.01527 -0.1874 0.4252 1.0000
8.500 1.7709 0.02350 0.01595 -0.1857 0.4189 1.0000
8.750 1.7881 0.02400 0.01648 -0.1841 0.4120 1.0000
9.000 1.8129 0.02458 0.01698 -0.1838 0.4054 1.0000
9.250 1.8222 0.02515 0.01773 -0.1809 0.3992 1.0000
9.500 1.8388 0.02567 0.01827 -0.1793 0.3932 1.0000
9.750 1.8580 0.02625 0.01885 -0.1781 0.3870 1.0000
10.000 1.8605 0.02690 0.01966 -0.1742 0.3810 1.0000
10.250 1.8725 0.02747 0.02027 -0.1719 0.3751 1.0000
10.500 1.8861 0.02814 0.02096 -0.1699 0.3693 1.0000
10.750 1.8871 0.02902 0.02201 -0.1663 0.3630 1.0000
11.000 1.8960 0.02974 0.02275 -0.1638 0.3567 1.0000
11.250 1.8998 0.03075 0.02387 -0.1608 0.3503 1.0000
11.500 1.9014 0.03186 0.02511 -0.1578 0.3434 1.0000
11.750 1.9088 0.03282 0.02605 -0.1555 0.3368 1.0000
12.000 1.9057 0.03439 0.02782 -0.1524 0.3290 1.0000
12.250 1.9101 0.03561 0.02903 -0.1500 0.3219 1.0000
12.500 1.9079 0.03743 0.03104 -0.1474 0.3135 1.0000
12.750 1.9095 0.03902 0.03261 -0.1451 0.3060 1.0000
13.000 1.9087 0.04101 0.03477 -0.1429 0.2974 1.0000
13.250 1.9084 0.04296 0.03673 -0.1408 0.2895 1.0000
13.500 1.9065 0.04523 0.03912 -0.1388 0.2803 1.0000
13.750 1.9030 0.04775 0.04170 -0.1369 0.2706 1.0000
14.000 1.8981 0.05052 0.04447 -0.1351 0.2607 1.0000
14.250 1.8935 0.05346 0.04750 -0.1336 0.2502 1.0000
14.500 1.8852 0.05689 0.05096 -0.1321 0.2384 1.0000
14.750 1.8744 0.06072 0.05480 -0.1306 0.2259 1.0000
15.000 1.8612 0.06500 0.05909 -0.1294 0.2124 1.0000
15.250 1.8461 0.06966 0.06377 -0.1284 0.1975 1.0000
15.500 1.8278 0.07492 0.06905 -0.1276 0.1781 1.0000
15.750 1.8033 0.08111 0.07519 -0.1270 0.1548 1.0000
16.000 1.7730 0.08825 0.08224 -0.1268 0.1318 1.0000
16.250 1.7415 0.09582 0.08973 -0.1271 0.1125 1.0000
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Polar data table (+)
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