GOE 225 (MVA H.35) AIRFOIL (goe225-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 225 (MVA H.35) AIRFOIL (goe225-il) Reynolds number: 50,000 Max Cl/Cd: 33.43 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe225-il-50000-n5.txt Download as CSV file: xf-goe225-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 225 (MVA H.35) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2074 0.12324 0.11649 -0.0499 0.9617 0.1293
-7.750 -0.2079 0.12163 0.11490 -0.0531 0.9545 0.1302
-7.500 -0.2075 0.11962 0.11291 -0.0555 0.9462 0.1306
-7.250 -0.2003 0.11677 0.11007 -0.0587 0.9386 0.1307
-6.250 -0.1527 0.09684 0.08998 -0.0728 0.9121 0.0880
-6.000 -0.1394 0.09397 0.08711 -0.0736 0.9058 0.0872
-5.750 -0.1271 0.09102 0.08415 -0.0750 0.8984 0.0860
-5.500 -0.1028 0.08688 0.07996 -0.0805 0.8934 0.0846
-5.250 -0.0948 0.08377 0.07685 -0.0826 0.8839 0.0835
-5.000 -0.0669 0.07900 0.07201 -0.0902 0.8779 0.0826
-4.750 -0.0429 0.07475 0.06769 -0.0967 0.8703 0.0832
-4.500 -0.0066 0.06920 0.06202 -0.1071 0.8631 0.0847
-4.250 0.0700 0.05811 0.05047 -0.1315 0.8599 0.0856
-4.000 0.1752 0.04686 0.03810 -0.1606 0.8590 0.0901
-3.750 0.2066 0.04545 0.03654 -0.1633 0.8506 0.0944
-3.500 0.2690 0.04170 0.03192 -0.1735 0.8462 0.1018
-3.250 0.3148 0.04026 0.03034 -0.1775 0.8420 0.1095
-3.000 0.3473 0.03924 0.02908 -0.1795 0.8336 0.1196
-2.750 0.3870 0.03822 0.02787 -0.1823 0.8272 0.1339
-2.500 0.4314 0.03746 0.02710 -0.1854 0.8231 0.1539
-2.250 0.4525 0.03754 0.02720 -0.1848 0.8114 0.1707
-2.000 0.4943 0.03698 0.02654 -0.1872 0.8065 0.1916
-1.750 0.5171 0.03703 0.02658 -0.1866 0.7954 0.2042
-1.500 0.5567 0.03649 0.02592 -0.1885 0.7898 0.2205
-1.250 0.5808 0.03655 0.02594 -0.1880 0.7789 0.2359
-1.000 0.6180 0.03613 0.02540 -0.1894 0.7728 0.2582
-0.750 0.6414 0.03627 0.02548 -0.1888 0.7618 0.2812
-0.500 0.6766 0.03594 0.02514 -0.1896 0.7555 0.3138
-0.250 0.6961 0.03629 0.02552 -0.1883 0.7438 0.3383
0.000 0.7312 0.03599 0.02516 -0.1889 0.7383 0.3701
0.250 0.7479 0.03655 0.02575 -0.1872 0.7262 0.3914
0.500 0.7830 0.03620 0.02537 -0.1877 0.7213 0.4178
0.750 0.7979 0.03690 0.02609 -0.1858 0.7091 0.4420
1.000 0.8325 0.03655 0.02576 -0.1860 0.7048 0.4760
1.250 0.8470 0.03730 0.02650 -0.1842 0.6929 0.4981
1.500 0.8835 0.03672 0.02588 -0.1848 0.6889 0.5199
1.750 0.8988 0.03748 0.02661 -0.1833 0.6776 0.5342
2.000 0.9355 0.03690 0.02597 -0.1841 0.6735 0.5533
2.250 0.9517 0.03764 0.02671 -0.1827 0.6630 0.5688
2.500 0.9865 0.03712 0.02617 -0.1832 0.6584 0.5903
2.750 1.0059 0.03769 0.02675 -0.1822 0.6496 0.6106
3.000 1.0363 0.03743 0.02653 -0.1822 0.6438 0.6368
3.250 1.0751 0.03654 0.02574 -0.1832 0.6403 0.6734
3.500 1.0845 0.03756 0.02694 -0.1809 0.6298 0.7121
3.750 1.1131 0.03672 0.02628 -0.1801 0.6251 1.0000
4.000 1.1289 0.03790 0.02738 -0.1789 0.6156 1.0000
4.250 1.1625 0.03783 0.02718 -0.1794 0.6101 1.0000
4.500 1.2012 0.03744 0.02668 -0.1805 0.6055 1.0000
4.750 1.2099 0.03894 0.02819 -0.1783 0.5952 1.0000
5.000 1.2521 0.03828 0.02741 -0.1796 0.5907 1.0000
5.250 1.2580 0.03994 0.02912 -0.1770 0.5802 1.0000
5.500 1.2971 0.03940 0.02850 -0.1779 0.5745 1.0000
5.750 1.3077 0.04069 0.02982 -0.1757 0.5646 1.0000
6.000 1.3427 0.04037 0.02946 -0.1761 0.5575 1.0000
6.250 1.3560 0.04146 0.03059 -0.1741 0.5480 1.0000
6.500 1.3859 0.04146 0.03057 -0.1739 0.5401 1.0000
6.750 1.3998 0.04251 0.03167 -0.1721 0.5309 1.0000
7.000 1.4243 0.04287 0.03206 -0.1713 0.5225 1.0000
7.250 1.4380 0.04393 0.03318 -0.1695 0.5136 1.0000
7.500 1.4577 0.04457 0.03387 -0.1682 0.5047 1.0000
7.750 1.4679 0.04587 0.03526 -0.1661 0.4956 1.0000
8.000 1.4855 0.04662 0.03608 -0.1646 0.4867 1.0000
8.250 1.4874 0.04851 0.03808 -0.1618 0.4769 1.0000
8.500 1.5086 0.04895 0.03858 -0.1606 0.4683 1.0000
8.750 1.4978 0.05187 0.04165 -0.1570 0.4575 1.0000
9.000 1.5273 0.05161 0.04145 -0.1565 0.4500 1.0000
9.250 1.5045 0.05571 0.04572 -0.1524 0.4382 1.0000
9.500 1.5438 0.05447 0.04450 -0.1523 0.4317 1.0000
9.750 1.5113 0.05966 0.04988 -0.1481 0.4190 1.0000
10.000 1.5301 0.06019 0.05049 -0.1468 0.4114 1.0000
10.250 1.5188 0.06372 0.05415 -0.1442 0.4006 1.0000
10.500 1.4962 0.06879 0.05936 -0.1418 0.3887 1.0000
10.750 1.5259 0.06796 0.05862 -0.1407 0.3828 1.0000
11.000 1.4910 0.07485 0.06566 -0.1386 0.3700 1.0000
11.250 1.5276 0.07311 0.06398 -0.1375 0.3657 1.0000
11.500 1.4841 0.08159 0.07262 -0.1360 0.3524 1.0000
11.750 1.5235 0.07925 0.07035 -0.1347 0.3490 1.0000
12.000 1.4735 0.08926 0.08049 -0.1342 0.3354 1.0000
12.250 1.5117 0.08682 0.07816 -0.1326 0.3327 1.0000
12.500 1.4551 0.09873 0.09018 -0.1336 0.3189 1.0000
12.750 1.4871 0.09701 0.08859 -0.1318 0.3167 1.0000
13.250 1.4516 0.10995 0.10173 -0.1330 0.2998 1.0000
13.750 1.4353 0.12003 0.11202 -0.1341 0.2847 1.0000
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Polar data table (+)
Polar graphs
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