GOE 226 (MVA H.36) AIRFOIL (goe226-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 226 (MVA H.36) AIRFOIL (goe226-il) Reynolds number: 100,000 Max Cl/Cd: 52.62 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe226-il-100000.txt Download as CSV file: xf-goe226-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.0084 0.10362 0.09878 -0.0887 0.9146 0.1219
-7.500 -0.0213 0.10430 0.09949 -0.0926 0.9054 0.1263
-7.250 -0.0552 0.10646 0.10173 -0.0914 0.8903 0.1270
-7.000 -0.0060 0.09849 0.09371 -0.0918 0.8907 0.1295
-6.750 0.0331 0.09410 0.08925 -0.0958 0.8885 0.1338
-6.500 0.0146 0.09438 0.08960 -0.0907 0.8770 0.1353
-6.250 0.0099 0.09475 0.08995 -0.1036 0.8679 0.1426
-6.000 -0.0155 0.09465 0.08993 -0.0989 0.8548 0.1430
-5.750 0.0181 0.08927 0.08453 -0.0943 0.8537 0.1453
-5.500 0.0579 0.08558 0.08077 -0.0974 0.8517 0.1522
-5.250 0.0317 0.08614 0.08140 -0.0916 0.8383 0.1540
-5.000 0.0624 0.08207 0.07727 -0.1019 0.8343 0.1612
-4.750 0.0351 0.08268 0.07796 -0.0948 0.8225 0.1617
-4.500 0.0834 0.07919 0.07434 -0.1122 0.8178 0.1759
-4.250 0.1060 0.07568 0.07084 -0.1078 0.8161 0.1781
-4.000 0.0794 0.07624 0.07147 -0.1009 0.8037 0.1787
-3.750 0.1309 0.07234 0.06746 -0.1123 0.8004 0.1942
-3.500 0.1530 0.07004 0.06516 -0.1098 0.7969 0.1985
-3.250 0.1473 0.06964 0.06479 -0.1072 0.7855 0.2032
-3.000 0.2012 0.06545 0.06049 -0.1166 0.7829 0.2156
-2.750 0.4567 0.03684 0.02898 -0.1910 0.7864 0.1434
-2.500 0.5020 0.03542 0.02759 -0.1936 0.7837 0.1522
-2.250 0.5538 0.03349 0.02533 -0.1973 0.7819 0.1627
-2.000 0.5643 0.03407 0.02591 -0.1952 0.7702 0.1699
-1.750 0.6096 0.03269 0.02442 -0.1974 0.7672 0.1841
-1.500 0.6555 0.03137 0.02303 -0.1993 0.7649 0.2031
-1.250 0.6702 0.03179 0.02347 -0.1976 0.7532 0.2155
-1.000 0.7122 0.03075 0.02242 -0.1988 0.7500 0.2383
-0.750 0.7551 0.02966 0.02127 -0.2002 0.7475 0.2658
-0.500 0.7705 0.03015 0.02185 -0.1984 0.7355 0.2856
-0.250 0.8112 0.02911 0.02086 -0.1993 0.7322 0.3226
0.000 0.8335 0.02922 0.02104 -0.1981 0.7220 0.3557
0.250 0.8701 0.02840 0.02025 -0.1983 0.7168 0.3926
0.500 0.9110 0.02734 0.01919 -0.1991 0.7136 0.4241
0.750 0.9306 0.02759 0.01946 -0.1975 0.7013 0.4466
1.000 0.9705 0.02660 0.01843 -0.1983 0.6972 0.4721
1.250 0.9913 0.02680 0.01868 -0.1970 0.6853 0.4915
1.500 1.0302 0.02595 0.01776 -0.1978 0.6804 0.5214
1.750 1.0511 0.02616 0.01805 -0.1964 0.6685 0.5452
2.000 1.0896 0.02538 0.01720 -0.1971 0.6629 0.5755
2.250 1.1103 0.02569 0.01756 -0.1959 0.6509 0.5978
2.500 1.1478 0.02509 0.01684 -0.1967 0.6453 0.6284
2.750 1.1667 0.02558 0.01740 -0.1954 0.6337 0.6570
3.000 1.2025 0.02497 0.01674 -0.1960 0.6280 0.7006
3.250 1.2187 0.02532 0.01732 -0.1943 0.6172 0.7565
3.500 1.2508 0.02476 0.01681 -0.1945 0.6112 1.0000
3.750 1.2716 0.02559 0.01757 -0.1939 0.6016 1.0000
4.000 1.3039 0.02565 0.01745 -0.1944 0.5950 1.0000
4.250 1.3267 0.02625 0.01799 -0.1937 0.5869 1.0000
4.500 1.3530 0.02651 0.01817 -0.1934 0.5792 1.0000
4.750 1.3829 0.02665 0.01818 -0.1935 0.5727 1.0000
5.000 1.4006 0.02737 0.01894 -0.1921 0.5640 1.0000
5.250 1.4349 0.02727 0.01869 -0.1928 0.5588 1.0000
5.500 1.4481 0.02833 0.01985 -0.1909 0.5508 1.0000
5.750 1.4747 0.02861 0.02009 -0.1906 0.5447 1.0000
6.000 1.5053 0.02879 0.02019 -0.1909 0.5396 1.0000
6.250 1.5162 0.02990 0.02144 -0.1886 0.5318 1.0000
6.500 1.5472 0.02996 0.02142 -0.1889 0.5265 1.0000
6.750 1.5660 0.03077 0.02229 -0.1877 0.5204 1.0000
7.000 1.5828 0.03160 0.02320 -0.1863 0.5139 1.0000
7.250 1.6176 0.03154 0.02305 -0.1871 0.5091 1.0000
7.500 1.6267 0.03281 0.02448 -0.1846 0.5022 1.0000
7.750 1.6489 0.03331 0.02501 -0.1838 0.4959 1.0000
8.000 1.6892 0.03309 0.02465 -0.1854 0.4909 1.0000
8.250 1.6856 0.03488 0.02669 -0.1813 0.4833 1.0000
8.500 1.7162 0.03508 0.02687 -0.1816 0.4777 1.0000
8.750 1.7378 0.03588 0.02772 -0.1808 0.4719 1.0000
9.000 1.7425 0.03734 0.02934 -0.1778 0.4650 1.0000
9.250 1.7844 0.03718 0.02910 -0.1796 0.4595 1.0000
9.500 1.7808 0.03909 0.03121 -0.1756 0.4525 1.0000
9.750 1.8001 0.03983 0.03201 -0.1745 0.4456 1.0000
10.000 1.8332 0.04010 0.03225 -0.1751 0.4388 1.0000
10.250 1.8201 0.04224 0.03462 -0.1699 0.4314 1.0000
10.500 1.8803 0.04112 0.03327 -0.1738 0.4230 1.0000
10.750 1.8446 0.04410 0.03660 -0.1657 0.4167 1.0000
11.000 1.9078 0.04264 0.03493 -0.1699 0.4070 1.0000
11.250 1.8730 0.04552 0.03811 -0.1620 0.4013 1.0000
11.500 1.8685 0.04711 0.03982 -0.1581 0.3944 1.0000
11.750 1.9124 0.04649 0.03913 -0.1597 0.3867 1.0000
12.000 1.8598 0.05088 0.04385 -0.1512 0.3817 1.0000
12.250 1.9248 0.04820 0.04100 -0.1543 0.3724 1.0000
12.500 1.8813 0.05235 0.04543 -0.1473 0.3675 1.0000
12.750 1.8237 0.05853 0.05189 -0.1408 0.3623 1.0000
13.000 1.9078 0.05312 0.04628 -0.1438 0.3531 1.0000
13.250 1.8199 0.06232 0.05588 -0.1361 0.3493 1.0000
13.750 1.8457 0.06295 0.05662 -0.1331 0.3352 1.0000
14.250 1.8638 0.06422 0.05801 -0.1298 0.3211 1.0000
15.000 1.7326 0.08649 0.08086 -0.1242 0.3050 1.0000
15.250 1.2453 0.18685 0.18108 -0.1633 0.2878 1.0000
15.500 1.2494 0.18917 0.18348 -0.1642 0.2792 1.0000
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Polar data table (+)
Polar graphs
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