GOE 241 (MVA PR.1) AIRFOIL (goe241-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 241 (MVA PR.1) AIRFOIL (goe241-il) Reynolds number: 50,000 Max Cl/Cd: 18.83 at α=0.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe241-il-50000-n5.txt Download as CSV file: xf-goe241-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 241 (MVA PR.1) 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
------ -------- --------- --------- -------- -------- --------
-9.000 0.1145 0.11402 0.10716 -0.1010 0.8705 0.1764
-8.750 0.1240 0.11172 0.10487 -0.1012 0.8619 0.1803
-8.250 0.1057 0.10170 0.09472 -0.1079 0.8445 0.1056
-8.000 0.0918 0.09734 0.09036 -0.1103 0.8349 0.0952
-7.750 0.1082 0.09435 0.08734 -0.1110 0.8288 0.0932
-7.500 0.1042 0.09238 0.08540 -0.1097 0.8177 0.0917
-7.250 0.1118 0.08863 0.08163 -0.1119 0.8123 0.0905
-7.000 0.0940 0.08737 0.08044 -0.1089 0.7985 0.0896
-6.500 0.0568 0.07522 0.06822 -0.1196 0.7772 0.0844
-6.250 0.0622 0.07056 0.06347 -0.1246 0.7686 0.0838
-6.000 0.0708 0.06505 0.05779 -0.1326 0.7584 0.0830
-5.750 0.1185 0.05654 0.04867 -0.1506 0.7544 0.0820
-5.500 0.1366 0.05348 0.04525 -0.1558 0.7419 0.0818
-5.250 0.1903 0.04931 0.04045 -0.1653 0.7375 0.0827
-5.000 0.2475 0.04599 0.03643 -0.1735 0.7345 0.0849
-4.750 0.2584 0.04550 0.03592 -0.1722 0.7218 0.0859
-4.500 0.2994 0.04367 0.03389 -0.1748 0.7175 0.0874
-4.250 0.3203 0.04308 0.03317 -0.1746 0.7078 0.0883
-4.000 0.3529 0.04199 0.03190 -0.1755 0.7013 0.0897
-3.750 0.3936 0.04065 0.03034 -0.1772 0.6976 0.0925
-3.500 0.4071 0.04086 0.03044 -0.1757 0.6862 0.0947
-3.250 0.4410 0.03993 0.02945 -0.1763 0.6813 0.0978
-3.000 0.4798 0.03887 0.02833 -0.1775 0.6781 0.1011
-2.750 0.4880 0.03957 0.02905 -0.1753 0.6661 0.1030
-2.500 0.5269 0.03879 0.02811 -0.1768 0.6619 0.1083
-2.250 0.5502 0.03886 0.02825 -0.1771 0.6536 0.1137
-2.000 0.5820 0.03865 0.02798 -0.1785 0.6468 0.1212
-1.750 0.6313 0.03759 0.02692 -0.1827 0.6432 0.1365
-1.250 0.6867 0.03821 0.02865 -0.1850 0.6288 0.3526
-1.000 0.7153 0.03876 0.02906 -0.1837 0.6248 0.4088
-0.750 0.7216 0.04039 0.03065 -0.1807 0.6162 0.4322
-0.500 0.7356 0.04148 0.03170 -0.1779 0.6097 0.4536
-0.250 0.7609 0.04190 0.03203 -0.1758 0.6063 0.4769
0.000 0.7576 0.04394 0.03412 -0.1721 0.5977 0.4897
0.250 0.7668 0.04524 0.03543 -0.1691 0.5915 0.5072
0.500 0.7954 0.04531 0.03538 -0.1683 0.5883 0.5254
0.750 0.8414 0.04469 0.03449 -0.1711 0.5861 0.5358
1.250 0.8506 0.04840 0.03819 -0.1678 0.5706 0.5435
1.500 0.8925 0.04797 0.03753 -0.1701 0.5684 0.5522
2.000 0.8917 0.05334 0.04297 -0.1669 0.5527 0.5602
2.250 0.9301 0.05288 0.04233 -0.1683 0.5504 0.5683
2.500 0.9712 0.05203 0.04132 -0.1695 0.5486 0.5757
3.000 0.9660 0.05813 0.04746 -0.1666 0.5316 0.5858
3.250 1.0141 0.05614 0.04529 -0.1676 0.5299 0.5945
3.750 1.0269 0.06004 0.04914 -0.1654 0.5123 0.6065
4.250 1.0390 0.06390 0.05299 -0.1629 0.4948 0.6183
4.500 1.0651 0.06389 0.05288 -0.1626 0.4901 0.6261
5.250 1.1129 0.06722 0.05615 -0.1607 0.4728 0.6481
5.750 1.1094 0.07356 0.06259 -0.1586 0.4554 0.6594
6.750 1.1047 0.08648 0.07572 -0.1553 0.4193 0.6831
7.000 1.1307 0.08624 0.07543 -0.1548 0.4160 0.6935
7.500 1.1389 0.09125 0.08055 -0.1534 0.3994 0.7085
8.000 1.1402 0.09739 0.08680 -0.1523 0.3817 0.7235
8.500 1.1103 0.10881 0.09838 -0.1525 0.3593 0.7337
9.000 1.1277 0.11333 0.10302 -0.1520 0.3487 0.7567
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Polar data table (+)
Polar graphs
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