GOE 226 (MVA H.36) AIRFOIL (goe226-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 226 (MVA H.36) AIRFOIL (goe226-il) Reynolds number: 500,000 Max Cl/Cd: 109.76 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe226-il-500000.txt Download as CSV file: xf-goe226-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.0187 0.09692 0.09399 -0.0871 0.8541 0.0428
-9.500 -0.0092 0.09451 0.09155 -0.0882 0.8490 0.0439
-8.750 -0.0971 0.02578 0.02186 -0.1797 0.8268 0.0429
-8.500 -0.0641 0.02343 0.01924 -0.1845 0.8208 0.0436
-8.250 -0.0319 0.02154 0.01704 -0.1881 0.8157 0.0446
-8.000 0.0000 0.01997 0.01519 -0.1908 0.8096 0.0456
-7.750 0.0313 0.01878 0.01371 -0.1927 0.8038 0.0463
-7.500 0.0617 0.01719 0.01185 -0.1945 0.7987 0.0472
-7.250 0.0910 0.01637 0.01101 -0.1953 0.7922 0.0480
-7.000 0.1206 0.01579 0.01034 -0.1960 0.7858 0.0489
-6.750 0.1504 0.01526 0.00967 -0.1966 0.7800 0.0500
-6.500 0.1802 0.01476 0.00908 -0.1972 0.7729 0.0512
-6.250 0.2102 0.01433 0.00848 -0.1977 0.7666 0.0524
-6.000 0.2402 0.01359 0.00761 -0.1984 0.7605 0.0535
-5.750 0.2699 0.01306 0.00706 -0.1989 0.7537 0.0549
-5.500 0.2995 0.01275 0.00666 -0.1993 0.7476 0.0563
-5.250 0.3293 0.01243 0.00629 -0.1997 0.7408 0.0579
-5.000 0.3589 0.01220 0.00594 -0.1999 0.7341 0.0596
-4.750 0.3888 0.01174 0.00542 -0.2004 0.7278 0.0618
-4.500 0.4185 0.01151 0.00518 -0.2008 0.7213 0.0640
-4.250 0.4481 0.01133 0.00492 -0.2010 0.7156 0.0663
-4.000 0.4779 0.01110 0.00462 -0.2014 0.7100 0.0688
-3.750 0.5076 0.01090 0.00443 -0.2017 0.7034 0.0721
-3.500 0.5369 0.01083 0.00428 -0.2018 0.6977 0.0757
-3.250 0.5666 0.01065 0.00408 -0.2022 0.6922 0.0799
-3.000 0.5961 0.01058 0.00400 -0.2024 0.6866 0.0845
-2.750 0.6255 0.01047 0.00385 -0.2026 0.6815 0.0903
-2.500 0.6548 0.01045 0.00380 -0.2028 0.6764 0.0971
-2.250 0.6843 0.01030 0.00367 -0.2031 0.6708 0.1052
-2.000 0.7132 0.01031 0.00360 -0.2031 0.6651 0.1124
-1.750 0.7426 0.01018 0.00348 -0.2035 0.6598 0.1225
-1.500 0.7719 0.01010 0.00341 -0.2037 0.6543 0.1305
-1.250 0.8009 0.01006 0.00335 -0.2038 0.6487 0.1400
-1.000 0.8298 0.01003 0.00331 -0.2040 0.6433 0.1514
-0.750 0.8589 0.00995 0.00331 -0.2042 0.6375 0.1689
-0.500 0.8877 0.00991 0.00334 -0.2044 0.6313 0.2046
-0.250 0.9162 0.00993 0.00340 -0.2044 0.6253 0.2417
0.000 0.9446 0.00994 0.00346 -0.2045 0.6183 0.2665
0.250 0.9724 0.01003 0.00353 -0.2044 0.6109 0.2877
0.500 1.0004 0.01007 0.00359 -0.2043 0.6029 0.3044
0.750 1.0279 0.01016 0.00365 -0.2042 0.5941 0.3183
1.000 1.0556 0.01020 0.00373 -0.2041 0.5848 0.3316
1.250 1.0824 0.01032 0.00380 -0.2038 0.5742 0.3438
1.500 1.1094 0.01040 0.00387 -0.2036 0.5608 0.3566
1.750 1.1356 0.01052 0.00398 -0.2033 0.5442 0.3716
2.000 1.1606 0.01072 0.00410 -0.2027 0.5239 0.3858
2.250 1.1851 0.01095 0.00426 -0.2021 0.5019 0.4008
2.500 1.2089 0.01125 0.00448 -0.2014 0.4833 0.4187
2.750 1.2327 0.01156 0.00473 -0.2007 0.4694 0.4382
3.000 1.2563 0.01189 0.00499 -0.2000 0.4586 0.4578
3.250 1.2816 0.01210 0.00522 -0.1996 0.4512 0.4778
3.500 1.3062 0.01236 0.00548 -0.1990 0.4452 0.4996
3.750 1.3306 0.01262 0.00575 -0.1985 0.4401 0.5243
4.000 1.3563 0.01277 0.00600 -0.1982 0.4359 0.5559
4.250 1.3812 0.01296 0.00628 -0.1977 0.4316 0.5980
4.500 1.4052 0.01319 0.00659 -0.1971 0.4274 0.6499
5.000 1.4499 0.01321 0.00707 -0.1951 0.4200 1.0000
5.250 1.4746 0.01345 0.00732 -0.1946 0.4164 1.0000
5.500 1.4985 0.01375 0.00759 -0.1940 0.4130 1.0000
5.750 1.5216 0.01410 0.00790 -0.1932 0.4096 1.0000
6.000 1.5449 0.01449 0.00824 -0.1926 0.4059 1.0000
6.250 1.5686 0.01471 0.00852 -0.1919 0.4033 1.0000
6.500 1.5917 0.01496 0.00880 -0.1912 0.4002 1.0000
6.750 1.6134 0.01526 0.00911 -0.1902 0.3963 1.0000
7.000 1.6325 0.01564 0.00946 -0.1888 0.3919 1.0000
7.250 1.6527 0.01604 0.00985 -0.1876 0.3877 1.0000
7.500 1.6723 0.01631 0.01018 -0.1863 0.3838 1.0000
7.750 1.6913 0.01663 0.01055 -0.1849 0.3792 1.0000
8.000 1.7090 0.01707 0.01098 -0.1834 0.3746 1.0000
8.250 1.7273 0.01755 0.01145 -0.1820 0.3703 1.0000
8.500 1.7463 0.01789 0.01188 -0.1808 0.3663 1.0000
8.750 1.7642 0.01832 0.01235 -0.1794 0.3615 1.0000
9.000 1.7795 0.01891 0.01293 -0.1778 0.3562 1.0000
9.250 1.7968 0.01941 0.01350 -0.1764 0.3510 1.0000
9.500 1.8140 0.01993 0.01407 -0.1751 0.3451 1.0000
9.750 1.8277 0.02066 0.01479 -0.1734 0.3392 1.0000
10.000 1.8443 0.02126 0.01546 -0.1721 0.3324 1.0000
10.250 1.8572 0.02208 0.01629 -0.1704 0.3241 1.0000
10.500 1.8712 0.02287 0.01712 -0.1689 0.3149 1.0000
10.750 1.8808 0.02397 0.01819 -0.1669 0.3046 1.0000
11.000 1.8914 0.02505 0.01927 -0.1651 0.2931 1.0000
11.250 1.8995 0.02632 0.02053 -0.1632 0.2809 1.0000
11.500 1.9046 0.02784 0.02202 -0.1609 0.2683 1.0000
11.750 1.9084 0.02950 0.02365 -0.1587 0.2569 1.0000
12.000 1.9109 0.03131 0.02542 -0.1564 0.2457 1.0000
12.250 1.9135 0.03315 0.02726 -0.1542 0.2337 1.0000
12.500 1.9148 0.03516 0.02926 -0.1520 0.2223 1.0000
12.750 1.9140 0.03743 0.03150 -0.1498 0.2105 1.0000
13.000 1.9114 0.03995 0.03399 -0.1476 0.1970 1.0000
13.250 1.9055 0.04289 0.03687 -0.1454 0.1782 1.0000
13.500 1.8897 0.04692 0.04075 -0.1429 0.1507 1.0000
13.750 1.8643 0.05216 0.04580 -0.1402 0.1209 1.0000
14.000 1.8385 0.05768 0.05121 -0.1379 0.0971 1.0000
14.250 1.8099 0.06379 0.05721 -0.1360 0.0717 1.0000
14.500 1.7828 0.06997 0.06332 -0.1345 0.0525 1.0000
14.750 1.7663 0.07503 0.06840 -0.1335 0.0454 1.0000
15.000 1.7550 0.07958 0.07302 -0.1328 0.0418 1.0000
15.250 1.7438 0.08420 0.07772 -0.1323 0.0395 1.0000
15.500 1.7327 0.08892 0.08253 -0.1320 0.0377 1.0000
15.750 1.7250 0.09321 0.08693 -0.1318 0.0365 1.0000
16.000 1.7157 0.09784 0.09166 -0.1318 0.0353 1.0000
16.250 1.7045 0.10280 0.09671 -0.1320 0.0343 1.0000
16.500 1.6921 0.10803 0.10204 -0.1325 0.0334 1.0000
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