GOE 228 (MVA H.38) AIRFOIL (goe228-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 228 (MVA H.38) AIRFOIL (goe228-il) Reynolds number: 200,000 Max Cl/Cd: 66.71 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe228-il-200000-n5.txt Download as CSV file: xf-goe228-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.3018 0.05845 0.05398 -0.1329 0.9197 0.0341
-12.000 -0.3363 0.04964 0.04485 -0.1414 0.9084 0.0341
-11.750 -0.3517 0.04428 0.03927 -0.1467 0.8969 0.0343
-11.500 -0.3486 0.04150 0.03640 -0.1491 0.8895 0.0347
-11.250 -0.3436 0.03902 0.03384 -0.1518 0.8802 0.0351
-11.000 -0.3300 0.03632 0.03097 -0.1564 0.8736 0.0357
-10.750 -0.3142 0.03381 0.02829 -0.1610 0.8650 0.0363
-10.500 -0.2940 0.03159 0.02581 -0.1647 0.8591 0.0371
-10.250 -0.2737 0.02971 0.02368 -0.1671 0.8530 0.0379
-10.000 -0.2517 0.02805 0.02176 -0.1690 0.8468 0.0387
-9.750 -0.2267 0.02658 0.02000 -0.1706 0.8420 0.0395
-9.500 -0.2019 0.02563 0.01904 -0.1714 0.8367 0.0403
-9.250 -0.1767 0.02481 0.01816 -0.1721 0.8307 0.0412
-9.000 -0.1498 0.02391 0.01714 -0.1731 0.8256 0.0421
-8.750 -0.1225 0.02301 0.01610 -0.1739 0.8208 0.0431
-8.500 -0.0965 0.02221 0.01517 -0.1744 0.8144 0.0440
-8.250 -0.0687 0.02144 0.01422 -0.1751 0.8088 0.0452
-8.000 -0.0401 0.02073 0.01348 -0.1759 0.8041 0.0464
-7.750 -0.0134 0.02020 0.01293 -0.1764 0.7972 0.0476
-7.500 0.0150 0.01962 0.01226 -0.1770 0.7911 0.0490
-7.250 0.0445 0.01903 0.01156 -0.1777 0.7859 0.0505
-7.000 0.0719 0.01852 0.01099 -0.1781 0.7786 0.0520
-6.750 0.1010 0.01803 0.01046 -0.1787 0.7721 0.0538
-6.500 0.1303 0.01762 0.00999 -0.1793 0.7657 0.0564
-6.250 0.1588 0.01722 0.00952 -0.1798 0.7579 0.0593
-6.000 0.1889 0.01678 0.00902 -0.1805 0.7513 0.0624
-5.750 0.2173 0.01645 0.00863 -0.1809 0.7427 0.0666
-5.500 0.2472 0.01603 0.00815 -0.1816 0.7348 0.0715
-5.250 0.2760 0.01574 0.00778 -0.1820 0.7257 0.0779
-5.000 0.3059 0.01536 0.00734 -0.1827 0.7169 0.0857
-4.750 0.3348 0.01504 0.00700 -0.1832 0.7065 0.0944
-4.500 0.3643 0.01475 0.00666 -0.1837 0.6964 0.1057
-4.250 0.3934 0.01446 0.00637 -0.1842 0.6850 0.1250
-4.000 0.4225 0.01416 0.00610 -0.1847 0.6735 0.1576
-3.750 0.4517 0.01387 0.00593 -0.1853 0.6618 0.2063
-3.500 0.4800 0.01381 0.00590 -0.1855 0.6495 0.2537
-3.250 0.5079 0.01386 0.00588 -0.1855 0.6370 0.2798
-3.000 0.5356 0.01394 0.00584 -0.1855 0.6251 0.2956
-2.750 0.5630 0.01403 0.00580 -0.1853 0.6136 0.3067
-2.500 0.5904 0.01411 0.00580 -0.1852 0.6019 0.3179
-2.250 0.6176 0.01423 0.00579 -0.1851 0.5914 0.3292
-2.000 0.6445 0.01434 0.00581 -0.1849 0.5809 0.3375
-1.750 0.6715 0.01445 0.00583 -0.1848 0.5708 0.3453
-1.250 0.7250 0.01469 0.00592 -0.1845 0.5525 0.3628
-1.000 0.7515 0.01484 0.00598 -0.1843 0.5444 0.3725
-0.750 0.7783 0.01496 0.00607 -0.1842 0.5364 0.3827
-0.500 0.8045 0.01510 0.00614 -0.1839 0.5285 0.3911
-0.250 0.8308 0.01523 0.00624 -0.1838 0.5212 0.3992
0.250 0.8828 0.01553 0.00644 -0.1833 0.5071 0.4131
0.500 0.9091 0.01565 0.00656 -0.1831 0.5004 0.4206
0.750 0.9349 0.01582 0.00669 -0.1828 0.4942 0.4286
1.000 0.9606 0.01600 0.00685 -0.1826 0.4887 0.4383
1.250 0.9865 0.01614 0.00703 -0.1824 0.4828 0.4490
1.500 1.0117 0.01633 0.00721 -0.1820 0.4771 0.4612
1.750 1.0365 0.01655 0.00742 -0.1816 0.4720 0.4744
2.000 1.0616 0.01672 0.00765 -0.1813 0.4663 0.4899
2.250 1.0858 0.01695 0.00789 -0.1807 0.4604 0.5079
2.500 1.1094 0.01722 0.00814 -0.1801 0.4550 0.5276
2.750 1.1335 0.01743 0.00840 -0.1796 0.4492 0.5471
3.000 1.1568 0.01768 0.00866 -0.1789 0.4437 0.5648
3.250 1.1796 0.01798 0.00892 -0.1782 0.4390 0.5808
3.500 1.2030 0.01823 0.00920 -0.1776 0.4344 0.5958
3.750 1.2259 0.01849 0.00950 -0.1769 0.4297 0.6105
4.000 1.2470 0.01877 0.00979 -0.1759 0.4251 0.6247
4.250 1.2673 0.01908 0.01008 -0.1747 0.4211 0.6380
4.500 1.2887 0.01934 0.01041 -0.1737 0.4169 0.6510
4.750 1.3101 0.01964 0.01075 -0.1729 0.4128 0.6639
5.000 1.3312 0.01996 0.01111 -0.1720 0.4089 0.6772
5.250 1.3517 0.02032 0.01147 -0.1709 0.4052 0.6913
5.500 1.3726 0.02065 0.01186 -0.1700 0.4014 0.7070
5.750 1.3930 0.02098 0.01227 -0.1691 0.3973 0.7249
6.000 1.4127 0.02132 0.01269 -0.1680 0.3935 0.7474
6.250 1.4313 0.02162 0.01311 -0.1666 0.3903 0.7873
6.500 1.4440 0.02177 0.01340 -0.1641 0.3877 1.0000
6.750 1.4648 0.02222 0.01387 -0.1634 0.3849 1.0000
7.000 1.4851 0.02268 0.01439 -0.1626 0.3819 1.0000
7.250 1.5049 0.02318 0.01491 -0.1617 0.3789 1.0000
7.500 1.5240 0.02370 0.01545 -0.1608 0.3761 1.0000
7.750 1.5430 0.02424 0.01600 -0.1598 0.3735 1.0000
8.000 1.5619 0.02479 0.01655 -0.1589 0.3711 1.0000
8.250 1.5808 0.02536 0.01714 -0.1580 0.3688 1.0000
8.500 1.5984 0.02596 0.01783 -0.1569 0.3658 1.0000
8.750 1.6152 0.02661 0.01855 -0.1558 0.3627 1.0000
9.000 1.6319 0.02727 0.01926 -0.1547 0.3598 1.0000
9.250 1.6487 0.02794 0.01997 -0.1536 0.3574 1.0000
9.500 1.6653 0.02863 0.02068 -0.1525 0.3550 1.0000
9.750 1.6820 0.02933 0.02141 -0.1515 0.3527 1.0000
10.000 1.6967 0.03015 0.02235 -0.1503 0.3499 1.0000
10.250 1.7110 0.03099 0.02330 -0.1491 0.3471 1.0000
10.500 1.7248 0.03187 0.02427 -0.1478 0.3443 1.0000
10.750 1.7383 0.03277 0.02524 -0.1466 0.3416 1.0000
11.000 1.7517 0.03369 0.02619 -0.1453 0.3389 1.0000
11.250 1.7656 0.03458 0.02710 -0.1442 0.3363 1.0000
11.500 1.7753 0.03578 0.02847 -0.1427 0.3331 1.0000
11.750 1.7837 0.03708 0.02991 -0.1412 0.3290 1.0000
12.000 1.7902 0.03849 0.03138 -0.1396 0.3241 1.0000
12.250 1.7975 0.03985 0.03274 -0.1380 0.3196 1.0000
12.500 1.8018 0.04160 0.03467 -0.1365 0.3144 1.0000
12.750 1.8052 0.04344 0.03661 -0.1350 0.3087 1.0000
13.000 1.8088 0.04528 0.03846 -0.1335 0.3034 1.0000
13.250 1.8106 0.04749 0.04084 -0.1321 0.2971 1.0000
13.500 1.8114 0.04979 0.04323 -0.1308 0.2907 1.0000
13.750 1.8111 0.05228 0.04582 -0.1295 0.2842 1.0000
14.000 1.8073 0.05525 0.04887 -0.1283 0.2754 1.0000
14.250 1.8025 0.05844 0.05217 -0.1272 0.2659 1.0000
14.500 1.7943 0.06211 0.05591 -0.1261 0.2546 1.0000
14.750 1.7822 0.06633 0.06018 -0.1252 0.2402 1.0000
15.000 1.7634 0.07149 0.06534 -0.1243 0.2216 1.0000
15.250 1.7355 0.07794 0.07175 -0.1236 0.2030 1.0000
15.500 1.7067 0.08469 0.07848 -0.1232 0.1908 1.0000
15.750 1.6816 0.09112 0.08493 -0.1231 0.1832 1.0000
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