GOE 222 (MVA H.33) AIRFOIL (goe222-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 222 (MVA H.33) AIRFOIL (goe222-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.19 at α=0.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe222-il-1000000.txt Download as CSV file: xf-goe222-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 222 (MVA H.33) 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
------ -------- --------- --------- -------- -------- --------
-17.250 -0.4754 0.09161 0.08913 -0.1223 0.9832 0.0221
-17.000 -0.5018 0.08298 0.08033 -0.1284 0.9807 0.0222
-16.750 -0.5170 0.07706 0.07428 -0.1321 0.9766 0.0224
-16.500 -0.5271 0.07199 0.06910 -0.1354 0.9727 0.0226
-16.250 -0.5332 0.06752 0.06452 -0.1385 0.9690 0.0227
-16.000 -0.5375 0.06359 0.06050 -0.1411 0.9648 0.0228
-15.750 -0.5454 0.05945 0.05625 -0.1436 0.9600 0.0230
-15.500 -0.5523 0.05598 0.05269 -0.1451 0.9553 0.0234
-15.250 -0.5486 0.05349 0.05016 -0.1466 0.9511 0.0236
-15.000 -0.5449 0.05095 0.04759 -0.1482 0.9463 0.0238
-14.750 -0.5409 0.04854 0.04513 -0.1496 0.9414 0.0240
-14.500 -0.5376 0.04605 0.04257 -0.1513 0.9364 0.0242
-14.250 -0.5332 0.04367 0.04015 -0.1530 0.9308 0.0244
-14.000 -0.5292 0.04129 0.03769 -0.1547 0.9249 0.0246
-13.750 -0.5243 0.03893 0.03525 -0.1565 0.9190 0.0249
-13.500 -0.5179 0.03666 0.03292 -0.1584 0.9118 0.0251
-13.250 -0.5103 0.03453 0.03068 -0.1601 0.9048 0.0254
-13.000 -0.5012 0.03243 0.02852 -0.1621 0.8960 0.0257
-12.750 -0.4918 0.03041 0.02640 -0.1640 0.8867 0.0260
-12.500 -0.4780 0.02844 0.02432 -0.1669 0.8755 0.0263
-12.250 -0.4583 0.02650 0.02226 -0.1706 0.8637 0.0266
-12.000 -0.4344 0.02468 0.02029 -0.1749 0.8503 0.0268
-11.750 -0.4160 0.02281 0.01830 -0.1773 0.8343 0.0273
-11.500 -0.3912 0.02130 0.01669 -0.1804 0.8179 0.0278
-11.250 -0.3642 0.02010 0.01536 -0.1832 0.8029 0.0281
-10.750 -0.3111 0.01860 0.01366 -0.1863 0.7809 0.0290
-10.500 -0.2844 0.01801 0.01296 -0.1875 0.7729 0.0296
-10.250 -0.2569 0.01741 0.01229 -0.1886 0.7672 0.0301
-10.000 -0.2295 0.01686 0.01165 -0.1895 0.7616 0.0305
-9.750 -0.2022 0.01641 0.01109 -0.1903 0.7558 0.0308
-9.500 -0.1736 0.01597 0.01060 -0.1911 0.7514 0.0311
-9.250 -0.1466 0.01511 0.00967 -0.1922 0.7469 0.0317
-9.000 -0.1187 0.01449 0.00901 -0.1932 0.7429 0.0325
-8.750 -0.0901 0.01411 0.00857 -0.1940 0.7388 0.0331
-8.500 -0.0608 0.01370 0.00813 -0.1949 0.7361 0.0336
-8.250 -0.0314 0.01332 0.00772 -0.1957 0.7333 0.0342
-8.000 -0.0020 0.01297 0.00732 -0.1964 0.7303 0.0348
-7.750 0.0275 0.01266 0.00696 -0.1971 0.7274 0.0354
-7.500 0.0568 0.01241 0.00665 -0.1977 0.7243 0.0358
-7.250 0.0866 0.01210 0.00626 -0.1985 0.7206 0.0365
-7.000 0.1168 0.01159 0.00571 -0.1995 0.7186 0.0376
-6.750 0.1467 0.01129 0.00540 -0.2003 0.7161 0.0384
-6.500 0.1767 0.01104 0.00512 -0.2009 0.7133 0.0393
-6.250 0.2065 0.01083 0.00487 -0.2015 0.7104 0.0403
-6.000 0.2363 0.01067 0.00466 -0.2020 0.7075 0.0412
-5.750 0.2664 0.01049 0.00442 -0.2027 0.7044 0.0422
-5.500 0.2969 0.01024 0.00413 -0.2035 0.7020 0.0442
-5.250 0.3270 0.01005 0.00393 -0.2041 0.7004 0.0461
-5.000 0.3571 0.00991 0.00377 -0.2046 0.6984 0.0479
-4.750 0.3875 0.00967 0.00353 -0.2053 0.6962 0.0520
-4.500 0.4178 0.00946 0.00333 -0.2059 0.6938 0.0598
-4.250 0.4491 0.00877 0.00294 -0.2074 0.6912 0.1451
-4.000 0.4797 0.00831 0.00275 -0.2085 0.6884 0.2292
-3.750 0.5098 0.00828 0.00275 -0.2090 0.6851 0.2550
-3.500 0.5395 0.00823 0.00274 -0.2094 0.6831 0.2691
-3.250 0.5692 0.00820 0.00272 -0.2098 0.6809 0.2781
-3.000 0.5987 0.00818 0.00272 -0.2102 0.6782 0.2863
-2.750 0.6282 0.00818 0.00270 -0.2105 0.6754 0.2929
-2.500 0.6574 0.00819 0.00271 -0.2108 0.6723 0.2999
-2.250 0.6865 0.00825 0.00273 -0.2110 0.6689 0.3062
-2.000 0.7158 0.00827 0.00274 -0.2114 0.6657 0.3120
-1.750 0.7449 0.00825 0.00276 -0.2116 0.6626 0.3182
-1.500 0.7738 0.00827 0.00278 -0.2118 0.6587 0.3239
-1.250 0.8021 0.00829 0.00278 -0.2119 0.6539 0.3292
-1.000 0.8301 0.00832 0.00279 -0.2120 0.6485 0.3333
-0.750 0.8588 0.00831 0.00281 -0.2122 0.6429 0.3373
-0.500 0.8864 0.00835 0.00282 -0.2122 0.6361 0.3407
-0.250 0.9138 0.00841 0.00283 -0.2121 0.6289 0.3433
0.000 0.9408 0.00843 0.00284 -0.2120 0.6187 0.3477
0.250 0.9672 0.00848 0.00288 -0.2118 0.6062 0.3517
0.500 0.9918 0.00861 0.00294 -0.2112 0.5892 0.3550
0.750 1.0137 0.00883 0.00304 -0.2100 0.5671 0.3582
1.000 1.0347 0.00912 0.00320 -0.2088 0.5434 0.3610
1.250 1.0554 0.00942 0.00338 -0.2075 0.5226 0.3637
1.500 1.0770 0.00967 0.00357 -0.2064 0.5063 0.3679
1.750 1.0982 0.00991 0.00376 -0.2052 0.4936 0.3715
2.250 1.1386 0.01036 0.00411 -0.2024 0.4734 0.3780
2.750 1.1827 0.01080 0.00450 -0.2004 0.4573 0.3855
3.000 1.2052 0.01105 0.00473 -0.1996 0.4506 0.3900
3.250 1.2280 0.01128 0.00496 -0.1988 0.4451 0.3942
3.500 1.2524 0.01146 0.00514 -0.1983 0.4410 0.3979
3.750 1.2758 0.01167 0.00536 -0.1977 0.4366 0.4020
4.000 1.2976 0.01194 0.00562 -0.1968 0.4318 0.4071
4.250 1.3203 0.01218 0.00588 -0.1960 0.4277 0.4120
4.500 1.3445 0.01236 0.00608 -0.1956 0.4247 0.4168
4.750 1.3677 0.01258 0.00633 -0.1949 0.4211 0.4228
5.000 1.3893 0.01286 0.00662 -0.1941 0.4170 0.4292
5.250 1.4094 0.01321 0.00697 -0.1929 0.4125 0.4352
5.500 1.4329 0.01342 0.00722 -0.1924 0.4097 0.4425
5.750 1.4564 0.01363 0.00749 -0.1919 0.4069 0.4509
6.000 1.4786 0.01390 0.00780 -0.1912 0.4036 0.4600
6.250 1.4997 0.01422 0.00815 -0.1903 0.4000 0.4717
6.500 1.5192 0.01461 0.00857 -0.1891 0.3959 0.4859
6.750 1.5406 0.01492 0.00894 -0.1884 0.3929 0.5031
7.000 1.5637 0.01516 0.00927 -0.1878 0.3903 0.5227
7.250 1.5854 0.01546 0.00964 -0.1871 0.3869 0.5427
7.500 1.6054 0.01585 0.01007 -0.1862 0.3825 0.5617
7.750 1.6216 0.01642 0.01065 -0.1846 0.3770 0.5798
8.000 1.6445 0.01667 0.01099 -0.1842 0.3728 0.6001
8.250 1.6641 0.01710 0.01147 -0.1832 0.3663 0.6219
8.500 1.6809 0.01767 0.01209 -0.1819 0.3584 0.6512
8.750 1.6962 0.01772 0.01269 -0.1801 0.3493 0.9892
9.000 1.7117 0.01841 0.01334 -0.1786 0.3393 1.0000
9.250 1.7237 0.01929 0.01417 -0.1767 0.3266 1.0000
9.500 1.7344 0.02028 0.01509 -0.1746 0.3095 1.0000
9.750 1.7363 0.02182 0.01648 -0.1714 0.2832 1.0000
10.000 1.7356 0.02358 0.01810 -0.1680 0.2602 1.0000
10.250 1.7396 0.02513 0.01957 -0.1654 0.2452 1.0000
10.500 1.7457 0.02660 0.02099 -0.1631 0.2345 1.0000
10.750 1.7558 0.02783 0.02222 -0.1614 0.2277 1.0000
11.000 1.7640 0.02922 0.02359 -0.1596 0.2210 1.0000
11.250 1.7744 0.03049 0.02488 -0.1580 0.2159 1.0000
11.500 1.7855 0.03174 0.02614 -0.1566 0.2114 1.0000
11.750 1.7936 0.03325 0.02765 -0.1550 0.2064 1.0000
12.000 1.8030 0.03468 0.02909 -0.1535 0.2018 1.0000
12.250 1.8152 0.03588 0.03033 -0.1524 0.1985 1.0000
12.500 1.8243 0.03737 0.03184 -0.1510 0.1942 1.0000
12.750 1.8310 0.03907 0.03355 -0.1495 0.1894 1.0000
13.000 1.8411 0.04052 0.03503 -0.1483 0.1857 1.0000
13.250 1.8514 0.04195 0.03649 -0.1472 0.1811 1.0000
13.500 1.8561 0.04389 0.03843 -0.1457 0.1755 1.0000
13.750 1.8638 0.04556 0.04012 -0.1444 0.1698 1.0000
14.000 1.8671 0.04766 0.04222 -0.1429 0.1620 1.0000
14.250 1.8692 0.04989 0.04442 -0.1413 0.1520 1.0000
14.500 1.8633 0.05294 0.04741 -0.1394 0.1384 1.0000
14.750 1.8518 0.05657 0.05096 -0.1372 0.1236 1.0000
15.000 1.8370 0.06064 0.05496 -0.1349 0.1094 1.0000
15.250 1.8221 0.06486 0.05914 -0.1329 0.0950 1.0000
15.500 1.7938 0.07066 0.06483 -0.1306 0.0701 1.0000
15.750 1.7679 0.07641 0.07053 -0.1287 0.0544 1.0000
16.000 1.7528 0.08113 0.07527 -0.1275 0.0468 1.0000
16.250 1.7424 0.08537 0.07956 -0.1267 0.0409 1.0000
16.500 1.7320 0.08964 0.08386 -0.1260 0.0347 1.0000
16.750 1.7187 0.09438 0.08860 -0.1254 0.0262 1.0000
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Polar data table (+)
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