GOE 227 (MVA H.37) AIRFOIL (goe227-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 227 (MVA H.37) AIRFOIL (goe227-il) Reynolds number: 200,000 Max Cl/Cd: 88.54 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe227-il-200000-n5.txt Download as CSV file: xf-goe227-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 227 (MVA H.37) 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.0155 0.09207 0.08760 -0.1037 0.8282 0.0403
-9.500 -0.0119 0.08849 0.08396 -0.1056 0.8210 0.0408
-9.250 -0.0134 0.08369 0.07914 -0.1087 0.8137 0.0419
-9.000 -0.0190 0.07776 0.07318 -0.1125 0.8061 0.0424
-8.750 -0.0168 0.07373 0.06911 -0.1149 0.7988 0.0428
-8.500 -0.0072 0.07142 0.06678 -0.1163 0.7904 0.0432
-8.000 -0.0179 0.02534 0.01910 -0.1919 0.7715 0.0489
-7.750 0.0138 0.02382 0.01734 -0.1948 0.7642 0.0499
-7.500 0.0435 0.02311 0.01655 -0.1962 0.7558 0.0508
-7.250 0.0740 0.02243 0.01572 -0.1977 0.7487 0.0521
-7.000 0.1053 0.02155 0.01465 -0.1995 0.7409 0.0538
-6.750 0.1377 0.02048 0.01325 -0.2016 0.7345 0.0558
-6.500 0.1693 0.01955 0.01208 -0.2032 0.7278 0.0573
-6.250 0.1993 0.01907 0.01154 -0.2041 0.7217 0.0587
-6.000 0.2297 0.01863 0.01100 -0.2050 0.7165 0.0604
-5.750 0.2603 0.01819 0.01042 -0.2060 0.7110 0.0628
-5.500 0.2914 0.01774 0.00975 -0.2070 0.7063 0.0654
-5.250 0.3219 0.01728 0.00920 -0.2079 0.7024 0.0676
-5.000 0.3522 0.01697 0.00885 -0.2087 0.6984 0.0699
-4.750 0.3826 0.01667 0.00845 -0.2094 0.6946 0.0727
-4.500 0.4131 0.01642 0.00805 -0.2101 0.6912 0.0758
-4.250 0.4437 0.01605 0.00763 -0.2109 0.6882 0.0788
-4.000 0.4741 0.01584 0.00737 -0.2116 0.6855 0.0819
-3.750 0.5042 0.01566 0.00713 -0.2122 0.6819 0.0855
-3.500 0.5341 0.01550 0.00687 -0.2128 0.6778 0.0886
-3.250 0.5645 0.01524 0.00661 -0.2135 0.6737 0.0923
-3.000 0.5946 0.01513 0.00641 -0.2140 0.6700 0.0964
-2.750 0.6244 0.01502 0.00626 -0.2145 0.6661 0.1002
-2.500 0.6544 0.01490 0.00613 -0.2151 0.6624 0.1044
-2.250 0.6844 0.01481 0.00604 -0.2156 0.6590 0.1097
-2.000 0.7144 0.01477 0.00592 -0.2161 0.6561 0.1154
-1.750 0.7449 0.01471 0.00583 -0.2168 0.6532 0.1222
-1.500 0.7744 0.01468 0.00579 -0.2172 0.6497 0.1319
-1.250 0.8041 0.01461 0.00574 -0.2177 0.6459 0.1448
-1.000 0.8340 0.01453 0.00569 -0.2183 0.6428 0.1623
-0.750 0.8646 0.01438 0.00569 -0.2191 0.6395 0.2059
-0.500 0.8943 0.01440 0.00584 -0.2196 0.6361 0.2855
-0.250 0.9228 0.01451 0.00594 -0.2198 0.6326 0.3135
0.000 0.9508 0.01462 0.00607 -0.2198 0.6289 0.3327
0.250 0.9790 0.01472 0.00619 -0.2199 0.6254 0.3467
0.500 1.0073 0.01482 0.00630 -0.2200 0.6220 0.3604
0.750 1.0359 0.01496 0.00641 -0.2202 0.6190 0.3757
1.000 1.0642 0.01509 0.00654 -0.2203 0.6160 0.3892
1.250 1.0912 0.01520 0.00672 -0.2202 0.6122 0.4025
1.500 1.1184 0.01530 0.00688 -0.2201 0.6081 0.4141
1.750 1.1460 0.01541 0.00700 -0.2201 0.6041 0.4251
2.000 1.1743 0.01554 0.00711 -0.2202 0.6005 0.4350
2.250 1.2012 0.01566 0.00730 -0.2201 0.5966 0.4457
2.750 1.2539 0.01588 0.00767 -0.2197 0.5869 0.4717
3.000 1.2814 0.01600 0.00778 -0.2196 0.5824 0.4847
3.250 1.3065 0.01612 0.00803 -0.2192 0.5767 0.4987
3.500 1.3319 0.01624 0.00822 -0.2188 0.5708 0.5146
3.750 1.3581 0.01635 0.00835 -0.2185 0.5654 0.5321
4.000 1.3823 0.01649 0.00862 -0.2179 0.5580 0.5501
4.250 1.4068 0.01660 0.00878 -0.2173 0.5504 0.5693
4.500 1.4305 0.01673 0.00902 -0.2166 0.5416 0.5898
4.750 1.4536 0.01684 0.00919 -0.2158 0.5325 0.6118
5.000 1.4757 0.01697 0.00945 -0.2148 0.5205 0.6369
5.250 1.4966 0.01710 0.00968 -0.2135 0.5066 0.6722
5.500 1.5150 0.01720 0.00989 -0.2118 0.4909 0.7527
5.750 1.5273 0.01725 0.01004 -0.2087 0.4760 1.0000
6.000 1.5438 0.01769 0.01039 -0.2068 0.4624 1.0000
6.250 1.5591 0.01821 0.01081 -0.2047 0.4511 1.0000
6.500 1.5717 0.01879 0.01130 -0.2021 0.4407 1.0000
6.750 1.5856 0.01940 0.01187 -0.1999 0.4314 1.0000
7.000 1.5987 0.02009 0.01249 -0.1975 0.4229 1.0000
7.250 1.6142 0.02072 0.01311 -0.1957 0.4153 1.0000
7.500 1.6290 0.02141 0.01377 -0.1938 0.4086 1.0000
7.750 1.6446 0.02209 0.01445 -0.1920 0.4028 1.0000
8.000 1.6602 0.02276 0.01516 -0.1904 0.3966 1.0000
8.250 1.6746 0.02352 0.01591 -0.1885 0.3907 1.0000
8.500 1.6892 0.02428 0.01669 -0.1868 0.3849 1.0000
8.750 1.7020 0.02510 0.01758 -0.1849 0.3777 1.0000
9.000 1.7124 0.02610 0.01854 -0.1827 0.3702 1.0000
9.250 1.7225 0.02710 0.01962 -0.1806 0.3611 1.0000
9.500 1.7301 0.02829 0.02079 -0.1782 0.3525 1.0000
9.750 1.7396 0.02941 0.02200 -0.1763 0.3436 1.0000
10.000 1.7464 0.03075 0.02334 -0.1740 0.3357 1.0000
10.250 1.7552 0.03201 0.02470 -0.1721 0.3267 1.0000
10.500 1.7608 0.03352 0.02622 -0.1700 0.3185 1.0000
10.750 1.7684 0.03495 0.02773 -0.1682 0.3094 1.0000
11.000 1.7725 0.03667 0.02948 -0.1661 0.2997 1.0000
11.250 1.7728 0.03875 0.03157 -0.1638 0.2876 1.0000
11.500 1.7737 0.04087 0.03373 -0.1617 0.2735 1.0000
11.750 1.7728 0.04324 0.03610 -0.1597 0.2586 1.0000
12.000 1.7691 0.04597 0.03881 -0.1576 0.2419 1.0000
12.250 1.7628 0.04908 0.04188 -0.1555 0.2218 1.0000
12.500 1.7506 0.05293 0.04562 -0.1534 0.1976 1.0000
12.750 1.7325 0.05756 0.05010 -0.1513 0.1679 1.0000
13.000 1.7118 0.06269 0.05506 -0.1493 0.1399 1.0000
13.250 1.6949 0.06752 0.05979 -0.1477 0.1196 1.0000
13.500 1.6806 0.07217 0.06439 -0.1464 0.1024 1.0000
13.750 1.6600 0.07772 0.06983 -0.1451 0.0672 1.0000
14.000 1.6349 0.08399 0.07596 -0.1441 0.0467 1.0000
14.250 1.6211 0.08898 0.08098 -0.1434 0.0390 1.0000
14.500 1.6120 0.09345 0.08553 -0.1430 0.0349 1.0000
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Polar data table (+)
Polar graphs
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