GOE 226 (MVA H.36) AIRFOIL (goe226-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 226 (MVA H.36) AIRFOIL (goe226-il) Reynolds number: 200,000 Max Cl/Cd: 78.67 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe226-il-200000-n5.txt Download as CSV file: xf-goe226-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.0025 0.09281 0.08849 -0.0946 0.8485 0.0409
-9.250 0.0035 0.08967 0.08533 -0.0962 0.8422 0.0410
-7.750 0.0051 0.03027 0.02500 -0.1745 0.8024 0.0469
-7.500 0.0454 0.02574 0.01989 -0.1847 0.7951 0.0482
-7.250 0.0798 0.02337 0.01705 -0.1892 0.7891 0.0496
-7.000 0.1124 0.02175 0.01502 -0.1918 0.7834 0.0509
-6.750 0.1412 0.02101 0.01425 -0.1927 0.7764 0.0519
-6.500 0.1711 0.02027 0.01339 -0.1937 0.7710 0.0529
-6.250 0.2013 0.01951 0.01248 -0.1947 0.7656 0.0541
-6.000 0.2314 0.01877 0.01156 -0.1956 0.7596 0.0555
-5.750 0.2619 0.01807 0.01062 -0.1965 0.7542 0.0571
-5.500 0.2916 0.01751 0.00998 -0.1971 0.7485 0.0588
-5.250 0.3209 0.01713 0.00956 -0.1976 0.7418 0.0605
-5.000 0.3507 0.01670 0.00901 -0.1981 0.7361 0.0625
-4.750 0.3804 0.01628 0.00846 -0.1985 0.7299 0.0645
-4.500 0.4099 0.01590 0.00802 -0.1990 0.7235 0.0666
-4.250 0.4395 0.01565 0.00770 -0.1993 0.7181 0.0693
-4.000 0.4688 0.01542 0.00740 -0.1996 0.7121 0.0725
-3.750 0.4983 0.01516 0.00710 -0.2000 0.7064 0.0755
-3.500 0.5277 0.01499 0.00685 -0.2002 0.7009 0.0791
-3.250 0.5567 0.01483 0.00662 -0.2004 0.6938 0.0838
-3.000 0.5858 0.01467 0.00644 -0.2006 0.6875 0.0885
-2.750 0.6151 0.01456 0.00621 -0.2008 0.6819 0.0945
-2.500 0.6440 0.01440 0.00608 -0.2011 0.6756 0.1009
-2.250 0.6730 0.01433 0.00591 -0.2012 0.6697 0.1080
-2.000 0.7023 0.01418 0.00574 -0.2015 0.6644 0.1159
-1.750 0.7309 0.01411 0.00565 -0.2016 0.6584 0.1239
-1.500 0.7598 0.01402 0.00555 -0.2018 0.6526 0.1330
-1.250 0.7887 0.01397 0.00546 -0.2020 0.6472 0.1431
-1.000 0.8170 0.01393 0.00546 -0.2021 0.6408 0.1563
-0.750 0.8455 0.01389 0.00545 -0.2022 0.6345 0.1763
-0.500 0.8738 0.01389 0.00549 -0.2023 0.6282 0.2067
-0.250 0.9014 0.01392 0.00558 -0.2022 0.6207 0.2386
0.000 0.9291 0.01399 0.00562 -0.2021 0.6136 0.2623
0.250 0.9564 0.01406 0.00571 -0.2019 0.6059 0.2803
0.500 0.9836 0.01415 0.00577 -0.2017 0.5981 0.2962
0.750 1.0106 0.01425 0.00587 -0.2015 0.5902 0.3114
1.000 1.0372 0.01434 0.00598 -0.2013 0.5812 0.3259
1.250 1.0635 0.01446 0.00609 -0.2009 0.5721 0.3399
1.500 1.0894 0.01458 0.00620 -0.2005 0.5615 0.3546
1.750 1.1151 0.01472 0.00634 -0.2001 0.5496 0.3706
2.000 1.1403 0.01487 0.00649 -0.1996 0.5370 0.3856
2.250 1.1651 0.01504 0.00665 -0.1990 0.5240 0.4025
2.500 1.1894 0.01525 0.00683 -0.1984 0.5110 0.4209
2.750 1.2133 0.01547 0.00704 -0.1977 0.4983 0.4408
3.000 1.2367 0.01573 0.00726 -0.1969 0.4870 0.4613
3.250 1.2593 0.01603 0.00751 -0.1960 0.4771 0.4812
3.500 1.2825 0.01631 0.00778 -0.1952 0.4677 0.5012
3.750 1.3046 0.01666 0.00809 -0.1943 0.4589 0.5226
4.000 1.3268 0.01698 0.00842 -0.1934 0.4501 0.5478
4.250 1.3481 0.01735 0.00877 -0.1923 0.4428 0.5774
4.500 1.3711 0.01761 0.00911 -0.1915 0.4371 0.6171
4.750 1.3936 0.01788 0.00945 -0.1907 0.4322 0.6679
5.000 1.4146 0.01804 0.00976 -0.1895 0.4278 0.7550
5.250 1.4334 0.01822 0.01003 -0.1878 0.4238 1.0000
5.500 1.4562 0.01857 0.01040 -0.1871 0.4196 1.0000
5.750 1.4784 0.01896 0.01078 -0.1863 0.4155 1.0000
6.000 1.5001 0.01938 0.01117 -0.1853 0.4118 1.0000
6.250 1.5214 0.01984 0.01157 -0.1844 0.4084 1.0000
6.500 1.5424 0.02024 0.01200 -0.1833 0.4052 1.0000
6.750 1.5626 0.02064 0.01245 -0.1822 0.4016 1.0000
7.000 1.5823 0.02107 0.01292 -0.1810 0.3978 1.0000
7.250 1.6017 0.02155 0.01341 -0.1798 0.3939 1.0000
7.500 1.6214 0.02207 0.01390 -0.1787 0.3902 1.0000
7.750 1.6403 0.02257 0.01444 -0.1774 0.3866 1.0000
8.000 1.6579 0.02307 0.01504 -0.1760 0.3827 1.0000
8.250 1.6755 0.02360 0.01564 -0.1747 0.3788 1.0000
8.500 1.6924 0.02419 0.01625 -0.1732 0.3748 1.0000
8.750 1.7092 0.02482 0.01686 -0.1718 0.3705 1.0000
9.000 1.7228 0.02548 0.01767 -0.1700 0.3652 1.0000
9.250 1.7361 0.02620 0.01846 -0.1682 0.3597 1.0000
9.500 1.7493 0.02697 0.01924 -0.1665 0.3547 1.0000
9.750 1.7623 0.02777 0.02014 -0.1648 0.3494 1.0000
10.000 1.7736 0.02866 0.02113 -0.1629 0.3431 1.0000
10.250 1.7836 0.02964 0.02212 -0.1610 0.3372 1.0000
10.500 1.7946 0.03064 0.02324 -0.1593 0.3306 1.0000
10.750 1.8042 0.03173 0.02440 -0.1575 0.3244 1.0000
11.000 1.8136 0.03288 0.02561 -0.1557 0.3186 1.0000
11.250 1.8221 0.03412 0.02696 -0.1539 0.3113 1.0000
11.500 1.8278 0.03557 0.02844 -0.1519 0.3040 1.0000
11.750 1.8338 0.03707 0.03003 -0.1501 0.2952 1.0000
12.000 1.8373 0.03879 0.03178 -0.1481 0.2870 1.0000
12.250 1.8391 0.04072 0.03374 -0.1462 0.2774 1.0000
12.500 1.8402 0.04279 0.03585 -0.1443 0.2677 1.0000
12.750 1.8384 0.04519 0.03824 -0.1423 0.2583 1.0000
13.000 1.8381 0.04758 0.04068 -0.1407 0.2482 1.0000
13.250 1.8366 0.05017 0.04329 -0.1390 0.2392 1.0000
13.500 1.8345 0.05289 0.04604 -0.1375 0.2306 1.0000
13.750 1.8343 0.05550 0.04871 -0.1362 0.2230 1.0000
14.000 1.8312 0.05849 0.05175 -0.1349 0.2150 1.0000
14.250 1.8291 0.06145 0.05478 -0.1338 0.2067 1.0000
14.500 1.8210 0.06515 0.05849 -0.1326 0.1973 1.0000
14.750 1.8152 0.06871 0.06211 -0.1317 0.1855 1.0000
15.000 1.8071 0.07260 0.06605 -0.1308 0.1732 1.0000
15.250 1.7945 0.07717 0.07063 -0.1301 0.1580 1.0000
15.500 1.7746 0.08279 0.07621 -0.1296 0.1399 1.0000
15.750 1.7505 0.08912 0.08249 -0.1294 0.1225 1.0000
16.000 1.7265 0.09566 0.08900 -0.1295 0.1079 1.0000
16.250 1.7034 0.10224 0.09558 -0.1299 0.0940 1.0000
16.500 1.6807 0.10889 0.10223 -0.1306 0.0782 1.0000
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Polar data table (+)
Polar graphs
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