GOE 227 (MVA H.37) AIRFOIL (goe227-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 227 (MVA H.37) AIRFOIL (goe227-il) Reynolds number: 200,000 Max Cl/Cd: 88 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe227-il-200000.txt Download as CSV file: xf-goe227-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 0.0224 0.10294 0.09912 -0.1076 0.9271 0.0713
-9.750 0.0050 0.10128 0.09745 -0.1147 0.9135 0.0736
-9.500 0.0143 0.09689 0.09304 -0.1149 0.9063 0.0743
-9.250 0.0343 0.09410 0.09021 -0.1124 0.8974 0.0753
-9.000 0.0488 0.09176 0.08782 -0.1117 0.8892 0.0765
-8.750 0.0588 0.08957 0.08559 -0.1118 0.8786 0.0781
-8.500 0.0669 0.08726 0.08324 -0.1125 0.8685 0.0803
-8.250 0.0555 0.08487 0.08080 -0.1193 0.8559 0.0847
-8.000 0.0524 0.08093 0.07685 -0.1234 0.8440 0.0854
-7.750 0.0737 0.07827 0.07412 -0.1200 0.8377 0.0865
-7.500 0.0912 0.07652 0.07233 -0.1186 0.8290 0.0879
-7.250 0.1051 0.07459 0.07033 -0.1187 0.8220 0.0900
-7.000 0.1145 0.07240 0.06813 -0.1200 0.8128 0.0928
-6.750 0.1124 0.06638 0.06206 -0.1362 0.8043 0.0985
-6.500 0.1261 0.06480 0.06048 -0.1326 0.7975 0.0994
-6.250 0.1628 0.04171 0.03689 -0.1762 0.7911 0.0847
-6.000 0.1857 0.03780 0.03293 -0.1797 0.7857 0.0825
-5.750 0.2437 0.02741 0.02149 -0.2003 0.7804 0.0812
-5.500 0.2840 0.02483 0.01828 -0.2055 0.7763 0.0842
-5.250 0.3204 0.02260 0.01563 -0.2090 0.7731 0.0866
-5.000 0.3504 0.02181 0.01480 -0.2102 0.7690 0.0893
-4.750 0.3807 0.02127 0.01416 -0.2112 0.7648 0.0931
-4.500 0.4136 0.02063 0.01322 -0.2127 0.7613 0.0970
-4.250 0.4461 0.01954 0.01198 -0.2142 0.7584 0.1006
-4.000 0.4772 0.01919 0.01155 -0.2150 0.7559 0.1051
-3.750 0.5070 0.01890 0.01116 -0.2157 0.7519 0.1097
-3.500 0.5373 0.01830 0.01045 -0.2165 0.7472 0.1139
-3.250 0.5676 0.01790 0.01004 -0.2171 0.7431 0.1190
-3.000 0.5991 0.01759 0.00959 -0.2177 0.7399 0.1243
-2.750 0.6288 0.01724 0.00920 -0.2183 0.7362 0.1295
-2.500 0.6577 0.01699 0.00902 -0.2187 0.7320 0.1354
-2.250 0.6878 0.01681 0.00876 -0.2192 0.7284 0.1418
-2.000 0.7191 0.01640 0.00839 -0.2200 0.7252 0.1500
-1.750 0.7505 0.01621 0.00810 -0.2206 0.7221 0.1595
-1.500 0.7796 0.01598 0.00803 -0.2212 0.7177 0.1741
-1.250 0.8108 0.01566 0.00790 -0.2222 0.7136 0.2068
-1.000 0.8422 0.01554 0.00805 -0.2230 0.7099 0.3160
-0.750 0.8724 0.01569 0.00815 -0.2232 0.7071 0.3592
-0.500 0.8998 0.01594 0.00839 -0.2232 0.7034 0.3832
-0.250 0.9270 0.01612 0.00859 -0.2231 0.6994 0.4008
0.000 0.9554 0.01623 0.00870 -0.2231 0.6958 0.4155
0.250 0.9848 0.01629 0.00875 -0.2233 0.6925 0.4303
0.500 1.0142 0.01640 0.00883 -0.2235 0.6892 0.4434
0.750 1.0399 0.01659 0.00908 -0.2232 0.6845 0.4559
1.000 1.0675 0.01673 0.00923 -0.2232 0.6801 0.4715
1.250 1.0968 0.01679 0.00929 -0.2233 0.6764 0.4855
1.500 1.1262 0.01688 0.00936 -0.2235 0.6727 0.4956
1.750 1.1514 0.01708 0.00961 -0.2231 0.6673 0.5065
2.000 1.1791 0.01713 0.00970 -0.2231 0.6623 0.5175
2.250 1.2097 0.01716 0.00967 -0.2234 0.6580 0.5299
2.500 1.2351 0.01736 0.00994 -0.2231 0.6526 0.5434
2.750 1.2617 0.01746 0.01010 -0.2229 0.6469 0.5586
3.000 1.2919 0.01747 0.01007 -0.2232 0.6418 0.5751
3.250 1.3172 0.01761 0.01032 -0.2228 0.6355 0.5932
3.500 1.3433 0.01764 0.01044 -0.2224 0.6287 0.6152
3.750 1.3741 0.01762 0.01041 -0.2229 0.6233 0.6443
4.000 1.3957 0.01773 0.01075 -0.2218 0.6155 0.6784
4.250 1.4219 0.01764 0.01078 -0.2212 0.6086 0.7356
4.500 1.4399 0.01738 0.01080 -0.2190 0.6012 1.0000
4.750 1.4657 0.01751 0.01088 -0.2187 0.5926 1.0000
5.000 1.4918 0.01766 0.01098 -0.2184 0.5847 1.0000
5.250 1.5152 0.01777 0.01110 -0.2176 0.5750 1.0000
5.500 1.5382 0.01791 0.01123 -0.2167 0.5655 1.0000
5.750 1.5620 0.01796 0.01126 -0.2158 0.5558 1.0000
6.000 1.5815 0.01815 0.01150 -0.2144 0.5440 1.0000
6.250 1.6032 0.01830 0.01164 -0.2132 0.5335 1.0000
6.500 1.6244 0.01846 0.01178 -0.2120 0.5229 1.0000
6.750 1.6429 0.01874 0.01209 -0.2104 0.5107 1.0000
7.000 1.6619 0.01903 0.01236 -0.2088 0.4995 1.0000
7.250 1.6809 0.01935 0.01260 -0.2073 0.4893 1.0000
7.500 1.6983 0.01979 0.01301 -0.2055 0.4788 1.0000
7.750 1.7152 0.02029 0.01347 -0.2038 0.4689 1.0000
8.000 1.7321 0.02082 0.01387 -0.2019 0.4587 1.0000
8.250 1.7428 0.02145 0.01449 -0.1991 0.4478 1.0000
8.500 1.7552 0.02215 0.01516 -0.1966 0.4374 1.0000
8.750 1.7716 0.02286 0.01572 -0.1949 0.4272 1.0000
9.000 1.7797 0.02365 0.01662 -0.1919 0.4184 1.0000
9.250 1.7964 0.02439 0.01726 -0.1903 0.4098 1.0000
9.500 1.8024 0.02529 0.01828 -0.1872 0.4012 1.0000
9.750 1.8164 0.02611 0.01903 -0.1853 0.3929 1.0000
10.000 1.8223 0.02709 0.02016 -0.1823 0.3853 1.0000
10.250 1.8352 0.02797 0.02096 -0.1804 0.3773 1.0000
10.500 1.8359 0.02923 0.02241 -0.1771 0.3689 1.0000
10.750 1.8425 0.03039 0.02354 -0.1745 0.3601 1.0000
11.000 1.8442 0.03182 0.02514 -0.1717 0.3515 1.0000
11.250 1.8483 0.03323 0.02655 -0.1691 0.3430 1.0000
11.500 1.8486 0.03496 0.02841 -0.1665 0.3330 1.0000
11.750 1.8472 0.03690 0.03042 -0.1638 0.3218 1.0000
12.000 1.8440 0.03908 0.03264 -0.1612 0.3099 1.0000
12.250 1.8386 0.04160 0.03520 -0.1586 0.2962 1.0000
12.500 1.8313 0.04449 0.03814 -0.1562 0.2784 1.0000
12.750 1.8187 0.04811 0.04173 -0.1537 0.2540 1.0000
13.000 1.8007 0.05249 0.04598 -0.1513 0.2244 1.0000
13.250 1.7771 0.05771 0.05101 -0.1490 0.1907 1.0000
13.500 1.7497 0.06361 0.05669 -0.1469 0.1543 1.0000
13.750 1.7213 0.06981 0.06269 -0.1450 0.1253 1.0000
14.000 1.6968 0.07577 0.06853 -0.1436 0.0999 1.0000
14.250 1.6689 0.08233 0.07491 -0.1424 0.0654 1.0000
14.500 1.6470 0.08832 0.08082 -0.1417 0.0545 1.0000
14.750 1.6311 0.09372 0.08626 -0.1412 0.0494 1.0000
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Polar data table (+)
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