GOE 228 (MVA H.38) AIRFOIL (goe228-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 228 (MVA H.38) AIRFOIL (goe228-il) Reynolds number: 500,000 Max Cl/Cd: 92.86 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe228-il-500000.txt Download as CSV file: xf-goe228-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 228 (MVA H.38) 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
------ -------- --------- --------- -------- -------- --------
-13.250 -0.4226 0.05265 0.04937 -0.1363 0.9442 0.0301
-13.000 -0.4420 0.04691 0.04344 -0.1411 0.9323 0.0303
-12.750 -0.4473 0.04313 0.03955 -0.1440 0.9225 0.0305
-12.500 -0.4454 0.04010 0.03643 -0.1469 0.9124 0.0308
-12.250 -0.4425 0.03717 0.03337 -0.1500 0.9035 0.0312
-12.000 -0.4357 0.03455 0.03064 -0.1536 0.8939 0.0316
-11.750 -0.4195 0.03202 0.02796 -0.1584 0.8870 0.0321
-11.500 -0.3992 0.02932 0.02505 -0.1643 0.8797 0.0326
-11.250 -0.3785 0.02728 0.02276 -0.1676 0.8739 0.0332
-11.000 -0.3556 0.02563 0.02086 -0.1700 0.8688 0.0338
-10.750 -0.3309 0.02441 0.01941 -0.1719 0.8631 0.0344
-10.500 -0.3085 0.02261 0.01749 -0.1730 0.8580 0.0351
-10.250 -0.2826 0.02175 0.01657 -0.1738 0.8535 0.0359
-10.000 -0.2562 0.02098 0.01576 -0.1746 0.8484 0.0366
-9.750 -0.2293 0.02017 0.01486 -0.1753 0.8432 0.0373
-9.500 -0.2019 0.01940 0.01395 -0.1761 0.8386 0.0381
-9.250 -0.1741 0.01870 0.01313 -0.1768 0.8338 0.0388
-9.000 -0.1457 0.01816 0.01247 -0.1774 0.8286 0.0395
-8.750 -0.1191 0.01708 0.01133 -0.1781 0.8236 0.0405
-8.250 -0.0622 0.01598 0.01016 -0.1792 0.8137 0.0423
-8.000 -0.0334 0.01549 0.00960 -0.1798 0.8082 0.0433
-7.750 -0.0041 0.01505 0.00906 -0.1803 0.8032 0.0444
-7.500 0.0252 0.01471 0.00864 -0.1808 0.7979 0.0453
-7.250 0.0541 0.01399 0.00792 -0.1816 0.7920 0.0469
-7.000 0.0838 0.01361 0.00749 -0.1822 0.7864 0.0483
-6.750 0.1134 0.01328 0.00710 -0.1827 0.7807 0.0498
-6.500 0.1430 0.01296 0.00673 -0.1832 0.7741 0.0514
-6.250 0.1731 0.01251 0.00624 -0.1839 0.7679 0.0538
-6.000 0.2027 0.01226 0.00597 -0.1843 0.7610 0.0567
-5.750 0.2325 0.01196 0.00561 -0.1848 0.7535 0.0601
-5.500 0.2624 0.01168 0.00531 -0.1853 0.7463 0.0650
-5.250 0.2923 0.01135 0.00497 -0.1859 0.7375 0.0721
-5.000 0.3222 0.01106 0.00464 -0.1864 0.7292 0.0815
-4.750 0.3519 0.01079 0.00435 -0.1869 0.7192 0.0919
-4.500 0.3815 0.01054 0.00409 -0.1874 0.7092 0.1043
-4.250 0.4108 0.01030 0.00386 -0.1879 0.6980 0.1261
-4.000 0.4404 0.00996 0.00364 -0.1885 0.6855 0.1718
-3.750 0.4696 0.00972 0.00355 -0.1890 0.6724 0.2323
-3.500 0.4979 0.00973 0.00353 -0.1891 0.6592 0.2632
-3.250 0.5258 0.00980 0.00353 -0.1891 0.6457 0.2814
-3.000 0.5537 0.00990 0.00354 -0.1891 0.6317 0.2954
-2.750 0.5815 0.01001 0.00358 -0.1890 0.6181 0.3084
-2.500 0.6090 0.01012 0.00363 -0.1889 0.6052 0.3197
-2.250 0.6362 0.01030 0.00367 -0.1888 0.5929 0.3297
-2.000 0.6637 0.01038 0.00373 -0.1887 0.5813 0.3379
-1.750 0.6913 0.01051 0.00377 -0.1887 0.5709 0.3444
-1.250 0.7461 0.01072 0.00388 -0.1886 0.5514 0.3581
-1.000 0.7727 0.01091 0.00394 -0.1884 0.5422 0.3648
-0.750 0.8005 0.01096 0.00400 -0.1884 0.5335 0.3714
-0.250 0.8545 0.01124 0.00416 -0.1882 0.5174 0.3855
0.000 0.8811 0.01135 0.00426 -0.1880 0.5099 0.3943
0.250 0.9082 0.01148 0.00435 -0.1879 0.5029 0.4037
0.500 0.9349 0.01157 0.00445 -0.1878 0.4953 0.4127
0.750 0.9610 0.01174 0.00456 -0.1876 0.4884 0.4208
1.000 0.9881 0.01181 0.00466 -0.1876 0.4816 0.4296
1.250 1.0139 0.01198 0.00479 -0.1873 0.4753 0.4399
1.500 1.0405 0.01209 0.00493 -0.1872 0.4697 0.4522
1.750 1.0669 0.01219 0.00508 -0.1870 0.4636 0.4680
2.000 1.0920 0.01238 0.00526 -0.1867 0.4575 0.4878
2.250 1.1179 0.01251 0.00546 -0.1864 0.4520 0.5121
2.500 1.1435 0.01266 0.00565 -0.1861 0.4462 0.5374
2.750 1.1677 0.01289 0.00587 -0.1856 0.4408 0.5594
3.000 1.1925 0.01309 0.00608 -0.1851 0.4359 0.5782
3.250 1.2174 0.01326 0.00628 -0.1847 0.4308 0.5945
3.500 1.2411 0.01349 0.00650 -0.1841 0.4259 0.6096
3.750 1.2635 0.01378 0.00676 -0.1832 0.4214 0.6229
4.000 1.2879 0.01391 0.00697 -0.1827 0.4176 0.6350
4.250 1.3102 0.01411 0.00718 -0.1818 0.4135 0.6464
4.500 1.3309 0.01434 0.00743 -0.1807 0.4095 0.6574
4.750 1.3518 0.01465 0.00772 -0.1796 0.4055 0.6676
5.250 1.3981 0.01508 0.00826 -0.1783 0.3986 0.6906
5.500 1.4204 0.01534 0.00856 -0.1776 0.3950 0.7028
5.750 1.4417 0.01564 0.00888 -0.1767 0.3916 0.7160
6.250 1.4850 0.01622 0.00958 -0.1751 0.3853 0.7507
6.500 1.5068 0.01639 0.00993 -0.1743 0.3822 0.7909
6.750 1.5218 0.01642 0.01020 -0.1721 0.3790 1.0000
7.000 1.5422 0.01682 0.01058 -0.1712 0.3757 1.0000
7.250 1.5616 0.01730 0.01101 -0.1701 0.3723 1.0000
7.500 1.5826 0.01769 0.01143 -0.1694 0.3696 1.0000
7.750 1.6037 0.01805 0.01183 -0.1686 0.3668 1.0000
8.000 1.6239 0.01845 0.01227 -0.1678 0.3638 1.0000
8.250 1.6434 0.01890 0.01273 -0.1668 0.3610 1.0000
8.500 1.6622 0.01940 0.01323 -0.1658 0.3583 1.0000
8.750 1.6804 0.01997 0.01378 -0.1647 0.3555 1.0000
9.000 1.7000 0.02044 0.01430 -0.1639 0.3533 1.0000
9.250 1.7191 0.02091 0.01484 -0.1630 0.3505 1.0000
9.500 1.7368 0.02145 0.01543 -0.1619 0.3470 1.0000
9.750 1.7528 0.02209 0.01609 -0.1607 0.3431 1.0000
10.000 1.7669 0.02289 0.01685 -0.1592 0.3389 1.0000
10.250 1.7846 0.02347 0.01752 -0.1583 0.3359 1.0000
10.500 1.8014 0.02411 0.01824 -0.1573 0.3322 1.0000
10.750 1.8161 0.02489 0.01905 -0.1560 0.3281 1.0000
11.000 1.8282 0.02584 0.02000 -0.1545 0.3240 1.0000
11.250 1.8435 0.02663 0.02086 -0.1534 0.3203 1.0000
11.500 1.8578 0.02749 0.02179 -0.1523 0.3152 1.0000
11.750 1.8687 0.02859 0.02290 -0.1509 0.3099 1.0000
12.000 1.8795 0.02971 0.02407 -0.1495 0.3052 1.0000
12.250 1.8923 0.03074 0.02518 -0.1483 0.2989 1.0000
12.500 1.8975 0.03236 0.02678 -0.1465 0.2917 1.0000
12.750 1.9091 0.03355 0.02806 -0.1454 0.2839 1.0000
13.000 1.9132 0.03535 0.02986 -0.1437 0.2754 1.0000
13.250 1.9168 0.03727 0.03180 -0.1421 0.2631 1.0000
13.500 1.9119 0.04000 0.03448 -0.1400 0.2444 1.0000
13.750 1.8917 0.04427 0.03862 -0.1371 0.2140 1.0000
14.000 1.8615 0.04976 0.04398 -0.1341 0.1884 1.0000
14.250 1.8415 0.05451 0.04871 -0.1320 0.1773 1.0000
14.500 1.8290 0.05862 0.05286 -0.1305 0.1713 1.0000
14.750 1.8149 0.06303 0.05731 -0.1292 0.1663 1.0000
15.000 1.8052 0.06705 0.06141 -0.1282 0.1619 1.0000
15.250 1.7971 0.07095 0.06539 -0.1274 0.1583 1.0000
15.500 1.7849 0.07539 0.06990 -0.1267 0.1549 1.0000
15.750 1.7707 0.08016 0.07473 -0.1261 0.1515 1.0000
16.000 1.7647 0.08397 0.07864 -0.1257 0.1480 1.0000
16.250 1.7587 0.08781 0.08257 -0.1254 0.1438 1.0000
16.500 1.7452 0.09263 0.08746 -0.1252 0.1394 1.0000
16.750 1.7319 0.09751 0.09240 -0.1251 0.1350 1.0000
17.000 1.7259 0.10151 0.09646 -0.1252 0.1267 1.0000
17.250 1.7105 0.10682 0.10179 -0.1255 0.1151 1.0000
17.500 1.6838 0.11375 0.10865 -0.1261 0.0952 1.0000
17.750 1.6515 0.12164 0.11641 -0.1273 0.0752 1.0000
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