GOE 440 AIRFOIL (goe440-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 440 AIRFOIL (goe440-il) Reynolds number: 200,000 Max Cl/Cd: 67.73 at α=2° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe440-il-200000-n5.txt Download as CSV file: xf-goe440-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 440 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
------ -------- --------- --------- -------- -------- --------
-12.750 0.1199 0.14701 0.14373 -0.0999 0.8984 0.0054
-12.500 0.1278 0.14448 0.14117 -0.1009 0.8894 0.0054
-12.250 0.1355 0.14195 0.13862 -0.1019 0.8799 0.0054
-12.000 0.1467 0.13609 0.13274 -0.1013 0.8714 0.0056
-11.750 0.1550 0.13295 0.12956 -0.1018 0.8632 0.0058
-11.500 0.1633 0.13012 0.12671 -0.1026 0.8539 0.0059
-11.250 0.1717 0.12738 0.12395 -0.1034 0.8446 0.0061
-11.000 0.1802 0.12468 0.12121 -0.1043 0.8351 0.0062
-10.750 0.1887 0.12201 0.11852 -0.1052 0.8245 0.0064
-10.500 0.1973 0.11938 0.11586 -0.1061 0.8132 0.0065
-10.250 0.2059 0.11676 0.11319 -0.1070 0.8017 0.0067
-10.000 0.2146 0.11415 0.11053 -0.1079 0.7900 0.0069
-9.750 0.2234 0.11157 0.10789 -0.1088 0.7783 0.0071
-9.500 0.2322 0.10902 0.10527 -0.1098 0.7669 0.0073
-9.250 0.2413 0.10650 0.10268 -0.1108 0.7556 0.0075
-9.000 0.2504 0.10399 0.10011 -0.1118 0.7448 0.0077
-8.750 0.2597 0.10153 0.09758 -0.1128 0.7346 0.0080
-8.500 0.2691 0.09911 0.09509 -0.1139 0.7247 0.0082
-8.250 0.2788 0.09671 0.09265 -0.1151 0.7153 0.0085
-8.000 0.2886 0.09441 0.09028 -0.1163 0.7066 0.0088
-7.750 0.2986 0.09225 0.08808 -0.1177 0.6977 0.0091
-7.500 0.3085 0.09026 0.08606 -0.1193 0.6891 0.0094
-7.250 0.3179 0.08845 0.08421 -0.1211 0.6805 0.0096
-7.000 0.3271 0.08659 0.08232 -0.1229 0.6718 0.0097
-6.750 0.3368 0.08462 0.08032 -0.1245 0.6637 0.0099
-6.500 0.3469 0.08246 0.07814 -0.1259 0.6550 0.0099
-6.250 0.3562 0.08037 0.07603 -0.1271 0.6470 0.0100
-6.000 0.3656 0.07830 0.07394 -0.1284 0.6388 0.0100
-5.750 0.3784 0.07593 0.07155 -0.1306 0.6305 0.0101
-5.250 0.3970 0.06917 0.06478 -0.1333 0.6141 0.0107
-5.000 0.4071 0.06647 0.06203 -0.1333 0.6054 0.0113
-4.750 0.4205 0.06403 0.05955 -0.1351 0.5961 0.0119
-4.500 0.4362 0.06155 0.05702 -0.1377 0.5872 0.0125
-4.250 0.4542 0.05899 0.05440 -0.1411 0.5784 0.0132
-4.000 0.4754 0.05625 0.05163 -0.1453 0.5687 0.0141
-3.750 0.5002 0.05332 0.04863 -0.1504 0.5592 0.0152
-3.500 0.5300 0.05014 0.04535 -0.1567 0.5491 0.0164
-3.250 0.5732 0.04632 0.04140 -0.1664 0.5384 0.0184
-3.000 0.6399 0.04162 0.03637 -0.1812 0.5276 0.0196
-2.750 0.6865 0.03811 0.03251 -0.1890 0.5176 0.0197
-2.500 0.7244 0.03309 0.02735 -0.1959 0.5079 0.0211
-2.250 0.7691 0.02996 0.02385 -0.2020 0.4981 0.0220
-1.750 0.8653 0.02407 0.01694 -0.2118 0.4801 0.0071
-1.500 0.9057 0.02234 0.01469 -0.2147 0.4725 0.0075
-1.250 0.9420 0.02121 0.01312 -0.2163 0.4653 0.0090
-1.000 0.9763 0.02018 0.01164 -0.2176 0.4589 0.0094
-0.750 1.0107 0.01916 0.01033 -0.2189 0.4523 0.0092
-0.500 1.0432 0.01853 0.00948 -0.2200 0.4462 0.0098
-0.250 1.0773 0.01809 0.00877 -0.2216 0.4405 0.0132
0.000 1.1144 0.01736 0.00870 -0.2245 0.4348 0.3397
0.500 1.1658 0.01775 0.00887 -0.2245 0.4254 0.4374
0.750 1.1909 0.01795 0.00897 -0.2244 0.4204 0.4685
1.000 1.2153 0.01816 0.00926 -0.2243 0.4160 0.5530
1.250 1.2397 0.01834 0.00953 -0.2241 0.4121 0.6346
1.500 1.2568 0.01863 0.00980 -0.2226 0.3966 0.6895
1.750 1.2734 0.01882 0.01008 -0.2209 0.3858 0.7764
2.000 1.2815 0.01892 0.01025 -0.2174 0.3716 1.0000
2.250 1.2872 0.01972 0.01074 -0.2142 0.3355 1.0000
2.500 1.2979 0.02057 0.01134 -0.2120 0.3085 1.0000
2.750 1.2915 0.02254 0.01274 -0.2075 0.2415 1.0000
3.250 1.2530 0.02905 0.01825 -0.1962 0.0271 1.0000
3.500 1.2690 0.02988 0.01909 -0.1952 0.0235 1.0000
3.750 1.2843 0.03078 0.02002 -0.1942 0.0200 1.0000
4.250 1.3115 0.03286 0.02227 -0.1918 0.0164 1.0000
4.500 1.3255 0.03390 0.02334 -0.1907 0.0195 1.0000
4.750 1.3393 0.03496 0.02444 -0.1896 0.0248 1.0000
5.000 1.3533 0.03602 0.02551 -0.1886 0.0298 1.0000
5.250 1.3668 0.03715 0.02666 -0.1876 0.0334 1.0000
5.500 1.3766 0.03863 0.02828 -0.1863 0.0330 1.0000
5.750 1.3845 0.04033 0.03011 -0.1849 0.0304 1.0000
6.250 1.3806 0.04582 0.03615 -0.1810 0.0228 1.0000
6.750 1.3872 0.05064 0.04124 -0.1785 0.0178 1.0000
7.000 1.3702 0.05551 0.04644 -0.1767 0.0173 1.0000
7.250 1.3940 0.05573 0.04658 -0.1765 0.0160 1.0000
7.500 1.3983 0.05827 0.04922 -0.1756 0.0145 1.0000
7.750 1.3970 0.06153 0.05264 -0.1747 0.0135 1.0000
8.000 1.3930 0.06525 0.05652 -0.1739 0.0127 1.0000
8.250 1.3871 0.06933 0.06077 -0.1731 0.0121 1.0000
8.500 1.3789 0.07381 0.06543 -0.1725 0.0116 1.0000
8.750 1.3681 0.07877 0.07057 -0.1720 0.0113 1.0000
9.000 1.3553 0.08421 0.07619 -0.1718 0.0109 1.0000
9.250 1.3409 0.09005 0.08221 -0.1718 0.0107 1.0000
9.500 1.3255 0.09615 0.08849 -0.1720 0.0105 1.0000
9.750 1.3096 0.10246 0.09497 -0.1724 0.0104 1.0000
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Polar data table (+)
Polar graphs
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