GOE 226 (MVA H.36) AIRFOIL (goe226-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 226 (MVA H.36) AIRFOIL (goe226-il) Reynolds number: 1,000,000 Max Cl/Cd: 135.52 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe226-il-1000000.txt Download as CSV file: xf-goe226-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.1272 0.11566 0.11336 -0.0740 0.8560 0.0275
-11.750 -0.1139 0.11410 0.11177 -0.0743 0.8516 0.0277
-11.500 -0.4357 0.03140 0.02826 -0.1547 0.8439 0.0309
-11.250 -0.3979 0.02541 0.02199 -0.1692 0.8393 0.0312
-11.000 -0.3562 0.02042 0.01662 -0.1818 0.8346 0.0318
-10.750 -0.3247 0.01898 0.01508 -0.1849 0.8301 0.0324
-10.500 -0.2942 0.01816 0.01421 -0.1866 0.8253 0.0328
-10.250 -0.2640 0.01751 0.01349 -0.1879 0.8206 0.0333
-10.000 -0.2339 0.01687 0.01273 -0.1892 0.8156 0.0338
-9.750 -0.2035 0.01615 0.01192 -0.1905 0.8110 0.0343
-9.500 -0.1732 0.01548 0.01115 -0.1917 0.8057 0.0348
-9.250 -0.1433 0.01492 0.01046 -0.1926 0.8002 0.0353
-9.000 -0.1132 0.01443 0.00987 -0.1934 0.7947 0.0357
-8.750 -0.0830 0.01372 0.00905 -0.1944 0.7886 0.0361
-8.500 -0.0531 0.01299 0.00822 -0.1953 0.7824 0.0370
-8.250 -0.0231 0.01263 0.00783 -0.1959 0.7764 0.0377
-8.000 0.0067 0.01230 0.00744 -0.1964 0.7697 0.0383
-7.750 0.0364 0.01200 0.00704 -0.1969 0.7633 0.0390
-7.500 0.0665 0.01167 0.00666 -0.1974 0.7565 0.0397
-7.250 0.0962 0.01141 0.00629 -0.1978 0.7490 0.0403
-7.000 0.1261 0.01118 0.00599 -0.1981 0.7415 0.0408
-6.750 0.1562 0.01066 0.00538 -0.1988 0.7332 0.0419
-6.500 0.1861 0.01039 0.00507 -0.1993 0.7256 0.0429
-6.250 0.2158 0.01023 0.00485 -0.1996 0.7170 0.0439
-6.000 0.2454 0.01007 0.00462 -0.1998 0.7091 0.0450
-5.750 0.2751 0.00992 0.00440 -0.2001 0.7010 0.0459
-5.500 0.3047 0.00978 0.00417 -0.2004 0.6941 0.0467
-5.250 0.3350 0.00944 0.00380 -0.2009 0.6871 0.0485
-5.000 0.3645 0.00933 0.00363 -0.2012 0.6802 0.0500
-4.750 0.3944 0.00921 0.00347 -0.2015 0.6747 0.0515
-4.500 0.4240 0.00914 0.00335 -0.2017 0.6690 0.0527
-4.250 0.4538 0.00893 0.00309 -0.2021 0.6633 0.0554
-4.000 0.4836 0.00883 0.00297 -0.2024 0.6580 0.0576
-3.750 0.5132 0.00876 0.00286 -0.2026 0.6523 0.0595
-3.500 0.5428 0.00864 0.00270 -0.2029 0.6469 0.0628
-3.250 0.5724 0.00857 0.00261 -0.2031 0.6419 0.0662
-3.000 0.6022 0.00848 0.00252 -0.2034 0.6370 0.0707
-2.750 0.6316 0.00845 0.00247 -0.2036 0.6321 0.0762
-2.500 0.6607 0.00843 0.00245 -0.2037 0.6271 0.0841
-2.250 0.6905 0.00837 0.00241 -0.2040 0.6231 0.0919
-2.000 0.7197 0.00837 0.00241 -0.2041 0.6184 0.0984
-1.750 0.7489 0.00834 0.00238 -0.2043 0.6133 0.1055
-1.500 0.7779 0.00836 0.00237 -0.2044 0.6084 0.1106
-1.250 0.8074 0.00833 0.00234 -0.2047 0.6035 0.1159
-1.000 0.8365 0.00831 0.00232 -0.2048 0.5976 0.1224
-0.750 0.8650 0.00835 0.00232 -0.2049 0.5913 0.1270
-0.500 0.8944 0.00830 0.00230 -0.2051 0.5844 0.1379
-0.250 0.9229 0.00831 0.00232 -0.2052 0.5760 0.1565
0.000 0.9521 0.00823 0.00236 -0.2055 0.5674 0.2024
0.250 0.9802 0.00828 0.00242 -0.2055 0.5562 0.2332
0.500 1.0079 0.00837 0.00249 -0.2055 0.5406 0.2543
0.750 1.0347 0.00853 0.00259 -0.2053 0.5153 0.2715
1.000 1.0591 0.00890 0.00277 -0.2047 0.4792 0.2852
1.250 1.0840 0.00923 0.00298 -0.2041 0.4562 0.2976
1.500 1.1099 0.00947 0.00316 -0.2038 0.4430 0.3091
2.000 1.1632 0.00983 0.00347 -0.2034 0.4275 0.3338
2.250 1.1900 0.00998 0.00362 -0.2032 0.4218 0.3465
2.500 1.2172 0.01010 0.00375 -0.2031 0.4175 0.3602
2.750 1.2439 0.01024 0.00391 -0.2029 0.4135 0.3771
3.250 1.2963 0.01058 0.00428 -0.2024 0.4056 0.4133
3.500 1.3237 0.01066 0.00443 -0.2023 0.4032 0.4348
3.750 1.3505 0.01077 0.00458 -0.2021 0.4004 0.4551
4.000 1.3768 0.01091 0.00476 -0.2019 0.3975 0.4750
4.250 1.4026 0.01107 0.00496 -0.2016 0.3946 0.4959
4.500 1.4277 0.01127 0.00518 -0.2011 0.3913 0.5163
4.750 1.4528 0.01145 0.00542 -0.2007 0.3883 0.5453
5.000 1.4795 0.01151 0.00561 -0.2006 0.3866 0.5925
5.250 1.5058 0.01159 0.00582 -0.2004 0.3845 0.6476
5.500 1.5315 0.01169 0.00602 -0.2001 0.3820 0.6981
5.750 1.5531 0.01146 0.00622 -0.1990 0.3791 1.0000
6.000 1.5766 0.01173 0.00645 -0.1983 0.3748 1.0000
6.250 1.5997 0.01200 0.00672 -0.1975 0.3707 1.0000
6.500 1.6252 0.01214 0.00688 -0.1972 0.3683 1.0000
6.750 1.6498 0.01231 0.00706 -0.1967 0.3645 1.0000
7.000 1.6724 0.01255 0.00730 -0.1959 0.3601 1.0000
7.250 1.6921 0.01287 0.00759 -0.1945 0.3560 1.0000
7.500 1.7136 0.01310 0.00784 -0.1935 0.3526 1.0000
7.750 1.7360 0.01330 0.00808 -0.1926 0.3487 1.0000
8.000 1.7564 0.01358 0.00837 -0.1915 0.3441 1.0000
8.250 1.7741 0.01401 0.00877 -0.1899 0.3385 1.0000
8.500 1.7957 0.01427 0.00906 -0.1890 0.3331 1.0000
8.750 1.8142 0.01467 0.00945 -0.1877 0.3257 1.0000
9.000 1.8321 0.01513 0.00990 -0.1863 0.3179 1.0000
9.250 1.8477 0.01572 0.01045 -0.1846 0.3071 1.0000
9.500 1.8634 0.01633 0.01103 -0.1830 0.2954 1.0000
9.750 1.8754 0.01717 0.01181 -0.1809 0.2810 1.0000
10.000 1.8854 0.01816 0.01273 -0.1787 0.2662 1.0000
10.250 1.8940 0.01928 0.01377 -0.1763 0.2518 1.0000
10.500 1.9020 0.02046 0.01489 -0.1739 0.2385 1.0000
10.750 1.9097 0.02169 0.01608 -0.1716 0.2266 1.0000
11.000 1.9159 0.02306 0.01739 -0.1692 0.2147 1.0000
11.250 1.9241 0.02432 0.01862 -0.1672 0.2042 1.0000
11.500 1.9306 0.02572 0.01999 -0.1650 0.1924 1.0000
11.750 1.9324 0.02750 0.02169 -0.1624 0.1765 1.0000
12.000 1.9227 0.03022 0.02424 -0.1588 0.1486 1.0000
12.250 1.9024 0.03391 0.02773 -0.1545 0.1179 1.0000
12.500 1.8832 0.03779 0.03147 -0.1508 0.0919 1.0000
12.750 1.8551 0.04279 0.03630 -0.1470 0.0601 1.0000
13.000 1.8369 0.04716 0.04059 -0.1443 0.0418 1.0000
13.250 1.8324 0.05027 0.04372 -0.1426 0.0365 1.0000
13.500 1.8304 0.05322 0.04671 -0.1412 0.0338 1.0000
13.750 1.8305 0.05600 0.04955 -0.1401 0.0319 1.0000
14.000 1.8309 0.05877 0.05238 -0.1390 0.0307 1.0000
14.250 1.8293 0.06180 0.05547 -0.1379 0.0295 1.0000
14.500 1.8249 0.06523 0.05897 -0.1369 0.0283 1.0000
14.750 1.8237 0.06834 0.06216 -0.1361 0.0275 1.0000
15.000 1.8234 0.07136 0.06525 -0.1353 0.0268 1.0000
15.250 1.8212 0.07461 0.06857 -0.1346 0.0260 1.0000
15.500 1.8162 0.07829 0.07233 -0.1340 0.0253 1.0000
15.750 1.8094 0.08226 0.07638 -0.1334 0.0246 1.0000
16.000 1.7996 0.08673 0.08093 -0.1330 0.0239 1.0000
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