GOE 228 (MVA H.38) AIRFOIL (goe228-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 228 (MVA H.38) AIRFOIL (goe228-il) Reynolds number: 1,000,000 Max Cl/Cd: 109.03 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe228-il-1000000-n5.txt Download as CSV file: xf-goe228-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -0.5829 0.09281 0.09026 -0.0960 0.9630 0.0175
-17.000 -0.6047 0.08585 0.08317 -0.1001 0.9557 0.0177
-16.750 -0.6237 0.07945 0.07666 -0.1039 0.9478 0.0179
-16.500 -0.6405 0.07360 0.07068 -0.1074 0.9393 0.0180
-16.250 -0.6545 0.06811 0.06508 -0.1109 0.9300 0.0181
-16.000 -0.6663 0.06311 0.05995 -0.1141 0.9209 0.0182
-15.750 -0.6769 0.05831 0.05504 -0.1173 0.9099 0.0183
-15.500 -0.6894 0.05337 0.04997 -0.1209 0.8979 0.0185
-15.250 -0.7002 0.04882 0.04530 -0.1244 0.8855 0.0187
-15.000 -0.7078 0.04466 0.04101 -0.1277 0.8737 0.0188
-14.750 -0.7123 0.04074 0.03698 -0.1311 0.8629 0.0190
-14.500 -0.7136 0.03707 0.03320 -0.1346 0.8535 0.0192
-14.250 -0.7131 0.03364 0.02966 -0.1380 0.8447 0.0194
-14.000 -0.7025 0.03045 0.02636 -0.1426 0.8378 0.0196
-13.750 -0.6850 0.02765 0.02347 -0.1474 0.8315 0.0199
-13.500 -0.6628 0.02524 0.02094 -0.1522 0.8254 0.0203
-13.250 -0.6367 0.02320 0.01879 -0.1569 0.8198 0.0207
-13.000 -0.6078 0.02146 0.01693 -0.1613 0.8132 0.0211
-12.750 -0.5782 0.02012 0.01545 -0.1648 0.8065 0.0214
-12.500 -0.5498 0.01924 0.01447 -0.1668 0.8016 0.0217
-12.250 -0.5216 0.01819 0.01335 -0.1690 0.7972 0.0221
-12.000 -0.4932 0.01745 0.01255 -0.1704 0.7927 0.0225
-11.750 -0.4647 0.01688 0.01191 -0.1716 0.7884 0.0229
-11.500 -0.4358 0.01639 0.01137 -0.1726 0.7847 0.0233
-11.250 -0.4067 0.01590 0.01084 -0.1735 0.7806 0.0238
-11.000 -0.3776 0.01543 0.01030 -0.1744 0.7762 0.0242
-10.750 -0.3486 0.01501 0.00981 -0.1752 0.7715 0.0246
-10.500 -0.3193 0.01464 0.00937 -0.1760 0.7674 0.0250
-10.250 -0.2897 0.01429 0.00896 -0.1767 0.7630 0.0253
-10.000 -0.2603 0.01384 0.00845 -0.1775 0.7579 0.0257
-9.750 -0.2309 0.01336 0.00791 -0.1784 0.7528 0.0262
-9.500 -0.2012 0.01299 0.00750 -0.1791 0.7482 0.0267
-9.250 -0.1713 0.01266 0.00714 -0.1798 0.7427 0.0272
-9.000 -0.1417 0.01237 0.00679 -0.1804 0.7364 0.0277
-8.750 -0.1119 0.01209 0.00645 -0.1810 0.7305 0.0281
-8.500 -0.0820 0.01184 0.00614 -0.1816 0.7234 0.0286
-8.250 -0.0525 0.01162 0.00585 -0.1821 0.7157 0.0291
-8.000 -0.0226 0.01140 0.00557 -0.1826 0.7066 0.0295
-7.750 0.0070 0.01116 0.00526 -0.1831 0.6970 0.0299
-7.500 0.0367 0.01092 0.00494 -0.1836 0.6856 0.0306
-7.250 0.0662 0.01073 0.00469 -0.1841 0.6730 0.0312
-7.000 0.0954 0.01059 0.00447 -0.1845 0.6593 0.0319
-6.750 0.1245 0.01049 0.00427 -0.1848 0.6450 0.0327
-6.500 0.1535 0.01041 0.00410 -0.1851 0.6300 0.0335
-6.250 0.1824 0.01035 0.00395 -0.1854 0.6145 0.0342
-6.000 0.2116 0.01026 0.00378 -0.1857 0.6001 0.0353
-5.750 0.2407 0.01018 0.00363 -0.1860 0.5866 0.0367
-5.500 0.2697 0.01013 0.00351 -0.1863 0.5741 0.0383
-5.000 0.3279 0.01003 0.00330 -0.1870 0.5508 0.0443
-4.750 0.3570 0.00998 0.00322 -0.1873 0.5402 0.0511
-4.500 0.3861 0.00993 0.00316 -0.1876 0.5302 0.0597
-4.250 0.4153 0.00990 0.00310 -0.1879 0.5223 0.0663
-4.000 0.4445 0.00987 0.00304 -0.1883 0.5143 0.0709
-3.750 0.4734 0.00988 0.00300 -0.1885 0.5064 0.0752
-3.500 0.5025 0.00988 0.00296 -0.1888 0.4986 0.0786
-3.000 0.5604 0.00987 0.00289 -0.1893 0.4841 0.0889
-2.750 0.5896 0.00980 0.00285 -0.1897 0.4775 0.1075
-2.500 0.6189 0.00965 0.00281 -0.1902 0.4715 0.1520
-2.250 0.6485 0.00953 0.00277 -0.1908 0.4661 0.1912
-2.000 0.6776 0.00945 0.00280 -0.1912 0.4599 0.2363
-1.750 0.7060 0.00950 0.00284 -0.1914 0.4541 0.2524
-1.500 0.7348 0.00953 0.00289 -0.1916 0.4482 0.2673
-1.250 0.7625 0.00964 0.00295 -0.1916 0.4402 0.2774
-1.000 0.7907 0.00972 0.00301 -0.1918 0.4331 0.2855
-0.750 0.8185 0.00982 0.00307 -0.1918 0.4261 0.2924
-0.500 0.8462 0.00992 0.00315 -0.1918 0.4206 0.3014
-0.250 0.8744 0.00999 0.00322 -0.1920 0.4166 0.3082
0.000 0.9023 0.01009 0.00328 -0.1920 0.4118 0.3128
0.250 0.9297 0.01019 0.00337 -0.1920 0.4068 0.3183
0.500 0.9571 0.01030 0.00347 -0.1920 0.4022 0.3247
1.000 1.0114 0.01052 0.00367 -0.1919 0.3910 0.3403
1.250 1.0379 0.01067 0.00378 -0.1918 0.3850 0.3471
1.500 1.0648 0.01078 0.00389 -0.1917 0.3795 0.3541
1.750 1.0911 0.01092 0.00402 -0.1915 0.3744 0.3610
2.000 1.1169 0.01109 0.00416 -0.1913 0.3698 0.3666
2.250 1.1436 0.01119 0.00427 -0.1912 0.3665 0.3724
2.500 1.1699 0.01131 0.00440 -0.1910 0.3628 0.3805
3.000 1.2205 0.01163 0.00472 -0.1904 0.3546 0.3973
3.250 1.2458 0.01177 0.00487 -0.1900 0.3516 0.4063
3.500 1.2713 0.01190 0.00503 -0.1897 0.3485 0.4175
3.750 1.2959 0.01204 0.00520 -0.1893 0.3450 0.4302
4.000 1.3184 0.01221 0.00539 -0.1885 0.3414 0.4466
4.250 1.3394 0.01239 0.00561 -0.1874 0.3379 0.4681
4.500 1.3626 0.01255 0.00584 -0.1867 0.3351 0.4980
4.750 1.3865 0.01272 0.00608 -0.1862 0.3325 0.5251
5.000 1.4098 0.01293 0.00633 -0.1856 0.3295 0.5435
5.250 1.4325 0.01317 0.00658 -0.1849 0.3262 0.5564
5.500 1.4545 0.01345 0.00688 -0.1841 0.3228 0.5675
5.750 1.4761 0.01375 0.00718 -0.1832 0.3195 0.5760
6.000 1.4989 0.01398 0.00746 -0.1826 0.3169 0.5848
6.250 1.5209 0.01426 0.00775 -0.1818 0.3137 0.5928
6.500 1.5421 0.01458 0.00810 -0.1810 0.3099 0.6013
6.750 1.5622 0.01496 0.00847 -0.1800 0.3061 0.6085
7.000 1.5826 0.01532 0.00886 -0.1790 0.3030 0.6150
7.250 1.6042 0.01563 0.00921 -0.1783 0.3004 0.6218
7.500 1.6247 0.01600 0.00960 -0.1774 0.2968 0.6283
7.750 1.6436 0.01645 0.01007 -0.1764 0.2921 0.6364
8.000 1.6621 0.01693 0.01056 -0.1753 0.2883 0.6442
8.250 1.6822 0.01734 0.01102 -0.1744 0.2854 0.6530
8.500 1.7007 0.01783 0.01154 -0.1734 0.2799 0.6634
8.750 1.7158 0.01852 0.01223 -0.1719 0.2720 0.6767
9.000 1.7306 0.01925 0.01296 -0.1704 0.2613 0.6922
9.250 1.7394 0.02036 0.01402 -0.1682 0.2442 0.7127
9.500 1.7269 0.02286 0.01631 -0.1636 0.1955 0.7469
9.750 1.7179 0.02472 0.01837 -0.1592 0.1705 1.0000
10.000 1.7248 0.02614 0.01978 -0.1572 0.1623 1.0000
10.250 1.7362 0.02728 0.02093 -0.1557 0.1587 1.0000
10.500 1.7462 0.02854 0.02220 -0.1542 0.1552 1.0000
10.750 1.7549 0.02991 0.02358 -0.1526 0.1510 1.0000
11.000 1.7666 0.03108 0.02479 -0.1514 0.1485 1.0000
11.250 1.7789 0.03224 0.02600 -0.1502 0.1471 1.0000
11.500 1.7902 0.03350 0.02729 -0.1491 0.1451 1.0000
11.750 1.8001 0.03490 0.02873 -0.1478 0.1431 1.0000
12.000 1.8084 0.03644 0.03031 -0.1465 0.1405 1.0000
12.250 1.8144 0.03823 0.03213 -0.1451 0.1378 1.0000
12.500 1.8212 0.03998 0.03392 -0.1438 0.1351 1.0000
12.750 1.8298 0.04161 0.03561 -0.1427 0.1334 1.0000
13.000 1.8388 0.04324 0.03728 -0.1417 0.1311 1.0000
13.250 1.8444 0.04519 0.03928 -0.1406 0.1275 1.0000
13.500 1.8458 0.04762 0.04172 -0.1393 0.1234 1.0000
13.750 1.8474 0.05008 0.04422 -0.1381 0.1192 1.0000
14.000 1.8462 0.05288 0.04704 -0.1369 0.1116 1.0000
14.250 1.8250 0.05793 0.05201 -0.1350 0.0931 1.0000
14.500 1.7918 0.06461 0.05864 -0.1331 0.0744 1.0000
14.750 1.7592 0.07152 0.06556 -0.1316 0.0598 1.0000
15.000 1.7284 0.07838 0.07245 -0.1306 0.0465 1.0000
15.250 1.6991 0.08530 0.07939 -0.1300 0.0351 1.0000
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Polar data table (+)
Polar graphs
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