GOE 228 (MVA H.38) AIRFOIL (goe228-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 228 (MVA H.38) AIRFOIL (goe228-il) Reynolds number: 1,000,000 Max Cl/Cd: 116.19 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe228-il-1000000.txt Download as CSV file: xf-goe228-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.5486 0.08343 0.08105 -0.1015 0.9924 0.0214
-16.000 -0.5708 0.07480 0.07226 -0.1085 0.9874 0.0215
-15.750 -0.5818 0.06799 0.06531 -0.1148 0.9825 0.0217
-15.500 -0.5912 0.06259 0.05979 -0.1190 0.9735 0.0218
-15.250 -0.5995 0.05800 0.05508 -0.1222 0.9633 0.0219
-15.000 -0.6075 0.05393 0.05089 -0.1247 0.9523 0.0220
-14.750 -0.6262 0.04899 0.04580 -0.1276 0.9396 0.0223
-14.500 -0.6325 0.04533 0.04205 -0.1300 0.9279 0.0225
-14.250 -0.6335 0.04218 0.03882 -0.1323 0.9170 0.0227
-14.000 -0.6312 0.03926 0.03580 -0.1347 0.9059 0.0230
-13.750 -0.6259 0.03644 0.03291 -0.1374 0.8953 0.0232
-13.500 -0.6189 0.03377 0.03012 -0.1402 0.8857 0.0234
-13.250 -0.6108 0.03117 0.02743 -0.1433 0.8758 0.0237
-13.000 -0.5945 0.02868 0.02482 -0.1475 0.8672 0.0240
-12.750 -0.5736 0.02638 0.02239 -0.1521 0.8589 0.0243
-12.500 -0.5485 0.02434 0.02021 -0.1569 0.8521 0.0247
-12.250 -0.5198 0.02256 0.01831 -0.1615 0.8465 0.0251
-12.000 -0.4907 0.02134 0.01695 -0.1648 0.8413 0.0255
-11.750 -0.4626 0.02057 0.01604 -0.1667 0.8361 0.0258
-11.500 -0.4383 0.01887 0.01428 -0.1690 0.8318 0.0265
-11.250 -0.4106 0.01811 0.01348 -0.1703 0.8272 0.0270
-11.000 -0.3825 0.01749 0.01278 -0.1715 0.8226 0.0275
-10.750 -0.3541 0.01692 0.01214 -0.1725 0.8181 0.0279
-10.500 -0.3253 0.01635 0.01152 -0.1735 0.8142 0.0285
-10.250 -0.2964 0.01586 0.01096 -0.1743 0.8098 0.0290
-10.000 -0.2674 0.01546 0.01048 -0.1751 0.8055 0.0295
-9.750 -0.2382 0.01513 0.01006 -0.1757 0.8009 0.0298
-9.500 -0.2096 0.01415 0.00903 -0.1770 0.7971 0.0306
-9.250 -0.1802 0.01358 0.00843 -0.1779 0.7928 0.0312
-9.000 -0.1507 0.01318 0.00798 -0.1786 0.7882 0.0318
-8.750 -0.1212 0.01286 0.00760 -0.1792 0.7834 0.0325
-8.500 -0.0912 0.01251 0.00722 -0.1799 0.7794 0.0333
-8.250 -0.0613 0.01218 0.00684 -0.1805 0.7744 0.0339
-8.000 -0.0316 0.01191 0.00650 -0.1811 0.7693 0.0343
-7.750 -0.0014 0.01143 0.00595 -0.1819 0.7643 0.0352
-7.500 0.0289 0.01102 0.00552 -0.1827 0.7589 0.0362
-7.250 0.0589 0.01075 0.00521 -0.1832 0.7528 0.0372
-7.000 0.0889 0.01054 0.00494 -0.1838 0.7470 0.0383
-6.750 0.1192 0.01031 0.00468 -0.1843 0.7402 0.0392
-6.500 0.1491 0.01006 0.00435 -0.1848 0.7328 0.0404
-6.250 0.1795 0.00980 0.00407 -0.1854 0.7251 0.0422
-6.000 0.2092 0.00963 0.00385 -0.1859 0.7160 0.0440
-5.750 0.2393 0.00945 0.00363 -0.1863 0.7065 0.0465
-5.500 0.2688 0.00931 0.00344 -0.1867 0.6957 0.0507
-5.250 0.2985 0.00917 0.00329 -0.1871 0.6831 0.0577
-5.000 0.3278 0.00907 0.00317 -0.1875 0.6697 0.0666
-4.750 0.3570 0.00900 0.00304 -0.1878 0.6559 0.0745
-4.500 0.3859 0.00897 0.00294 -0.1880 0.6422 0.0807
-4.250 0.4147 0.00894 0.00284 -0.1882 0.6277 0.0870
-4.000 0.4434 0.00890 0.00276 -0.1885 0.6131 0.0959
-3.750 0.4726 0.00880 0.00267 -0.1889 0.5992 0.1160
-3.500 0.5018 0.00863 0.00258 -0.1894 0.5865 0.1590
-3.250 0.5309 0.00847 0.00252 -0.1899 0.5747 0.2087
-3.000 0.5598 0.00844 0.00253 -0.1902 0.5633 0.2444
-2.750 0.5886 0.00848 0.00256 -0.1904 0.5533 0.2641
-2.250 0.6455 0.00863 0.00265 -0.1907 0.5339 0.2903
-2.000 0.6735 0.00873 0.00270 -0.1907 0.5244 0.3009
-1.750 0.7022 0.00881 0.00275 -0.1909 0.5162 0.3094
-1.500 0.7299 0.00892 0.00281 -0.1909 0.5076 0.3168
-1.250 0.7588 0.00898 0.00285 -0.1911 0.5010 0.3227
-1.000 0.7866 0.00910 0.00291 -0.1911 0.4931 0.3277
-0.750 0.8148 0.00918 0.00296 -0.1912 0.4858 0.3343
-0.500 0.8427 0.00928 0.00303 -0.1913 0.4780 0.3415
-0.250 0.8702 0.00940 0.00311 -0.1913 0.4712 0.3467
0.000 0.8986 0.00946 0.00317 -0.1914 0.4653 0.3533
0.250 0.9258 0.00959 0.00326 -0.1914 0.4584 0.3596
0.500 0.9535 0.00970 0.00334 -0.1914 0.4522 0.3660
0.750 0.9812 0.00978 0.00342 -0.1915 0.4458 0.3758
1.000 1.0076 0.00994 0.00354 -0.1913 0.4391 0.3842
1.250 1.0356 0.01000 0.00362 -0.1914 0.4344 0.3927
1.500 1.0629 0.01011 0.00372 -0.1914 0.4292 0.4009
1.750 1.0893 0.01025 0.00384 -0.1912 0.4237 0.4101
2.000 1.1163 0.01035 0.00396 -0.1912 0.4190 0.4212
2.250 1.1434 0.01044 0.00408 -0.1912 0.4139 0.4359
2.500 1.1694 0.01057 0.00423 -0.1910 0.4085 0.4552
3.000 1.2222 0.01079 0.00456 -0.1907 0.4000 0.5123
3.250 1.2481 0.01093 0.00473 -0.1905 0.3957 0.5375
3.500 1.2728 0.01111 0.00492 -0.1901 0.3912 0.5562
3.750 1.2973 0.01131 0.00512 -0.1896 0.3869 0.5713
4.000 1.3231 0.01143 0.00528 -0.1893 0.3837 0.5835
4.250 1.3478 0.01160 0.00546 -0.1889 0.3799 0.5943
4.500 1.3704 0.01181 0.00566 -0.1880 0.3758 0.6048
4.750 1.3897 0.01206 0.00590 -0.1866 0.3713 0.6135
5.000 1.4134 0.01220 0.00609 -0.1859 0.3685 0.6223
5.250 1.4368 0.01239 0.00630 -0.1853 0.3651 0.6301
5.500 1.4594 0.01262 0.00654 -0.1845 0.3613 0.6382
5.750 1.4808 0.01292 0.00683 -0.1836 0.3575 0.6457
6.000 1.5026 0.01319 0.00713 -0.1828 0.3541 0.6543
6.250 1.5261 0.01339 0.00737 -0.1822 0.3517 0.6631
6.500 1.5489 0.01362 0.00765 -0.1816 0.3488 0.6725
6.750 1.5707 0.01390 0.00795 -0.1808 0.3458 0.6817
7.000 1.5914 0.01423 0.00831 -0.1799 0.3427 0.6926
7.250 1.6111 0.01461 0.00871 -0.1788 0.3392 0.7056
7.500 1.6336 0.01485 0.00904 -0.1782 0.3368 0.7248
7.750 1.6561 0.01507 0.00939 -0.1777 0.3342 0.7630
8.000 1.6728 0.01508 0.00974 -0.1759 0.3316 1.0000
8.250 1.6924 0.01551 0.01016 -0.1749 0.3279 1.0000
8.500 1.7093 0.01607 0.01070 -0.1736 0.3231 1.0000
8.750 1.7309 0.01641 0.01107 -0.1730 0.3201 1.0000
9.000 1.7509 0.01683 0.01151 -0.1721 0.3159 1.0000
9.250 1.7688 0.01736 0.01204 -0.1710 0.3117 1.0000
9.500 1.7847 0.01802 0.01268 -0.1696 0.3070 1.0000
9.750 1.8048 0.01845 0.01315 -0.1689 0.3034 1.0000
10.000 1.8223 0.01903 0.01374 -0.1678 0.2979 1.0000
10.250 1.8366 0.01981 0.01451 -0.1663 0.2924 1.0000
10.500 1.8542 0.02041 0.01513 -0.1653 0.2873 1.0000
10.750 1.8671 0.02131 0.01601 -0.1638 0.2786 1.0000
11.000 1.8803 0.02221 0.01689 -0.1623 0.2690 1.0000
11.250 1.8887 0.02344 0.01807 -0.1604 0.2557 1.0000
11.500 1.8842 0.02557 0.02004 -0.1570 0.2274 1.0000
11.750 1.8567 0.02948 0.02366 -0.1516 0.1823 1.0000
12.000 1.8517 0.03193 0.02605 -0.1488 0.1699 1.0000
12.250 1.8528 0.03399 0.02812 -0.1467 0.1625 1.0000
12.500 1.8577 0.03581 0.02996 -0.1450 0.1588 1.0000
12.750 1.8604 0.03784 0.03202 -0.1433 0.1550 1.0000
13.000 1.8622 0.04002 0.03424 -0.1417 0.1506 1.0000
13.250 1.8697 0.04174 0.03602 -0.1405 0.1482 1.0000
13.500 1.8761 0.04360 0.03793 -0.1394 0.1456 1.0000
13.750 1.8792 0.04579 0.04017 -0.1381 0.1425 1.0000
14.000 1.8775 0.04851 0.04292 -0.1366 0.1386 1.0000
14.250 1.8786 0.05105 0.04552 -0.1355 0.1350 1.0000
14.500 1.8837 0.05318 0.04771 -0.1346 0.1309 1.0000
14.750 1.8780 0.05654 0.05107 -0.1333 0.1245 1.0000
15.000 1.8725 0.05990 0.05446 -0.1322 0.1152 1.0000
15.250 1.8477 0.06560 0.06008 -0.1307 0.0972 1.0000
15.500 1.8138 0.07260 0.06704 -0.1293 0.0799 1.0000
15.750 1.7783 0.08002 0.07447 -0.1283 0.0664 1.0000
16.000 1.7446 0.08745 0.08192 -0.1277 0.0540 1.0000
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Polar data table (+)
Polar graphs
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