GOE 440 AIRFOIL (goe440-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 440 AIRFOIL (goe440-il) Reynolds number: 1,000,000 Max Cl/Cd: 100.28 at α=0.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe440-il-1000000-n5.txt Download as CSV file: xf-goe440-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 0.0461 0.16026 0.15788 -0.0817 0.7929 0.0011
-14.000 0.0552 0.15739 0.15489 -0.0829 0.7700 0.0011
-13.750 0.0646 0.15450 0.15190 -0.0842 0.7517 0.0011
-13.500 0.0740 0.15161 0.14892 -0.0856 0.7360 0.0011
-13.250 0.0835 0.14872 0.14596 -0.0870 0.7227 0.0012
-13.000 0.0932 0.14591 0.14309 -0.0884 0.7113 0.0012
-12.750 0.1026 0.14308 0.14022 -0.0898 0.7020 0.0012
-12.500 0.1120 0.14024 0.13734 -0.0912 0.6938 0.0012
-12.250 0.1215 0.13737 0.13444 -0.0926 0.6858 0.0012
-12.000 0.1310 0.13455 0.13158 -0.0940 0.6783 0.0012
-11.750 0.1405 0.13175 0.12875 -0.0954 0.6706 0.0012
-11.500 0.1499 0.12896 0.12592 -0.0967 0.6634 0.0012
-11.250 0.1594 0.12617 0.12311 -0.0981 0.6557 0.0012
-11.000 0.1690 0.12340 0.12030 -0.0994 0.6480 0.0012
-10.750 0.1786 0.12066 0.11752 -0.1008 0.6405 0.0012
-10.500 0.1882 0.11793 0.11477 -0.1021 0.6341 0.0012
-10.250 0.1979 0.11520 0.11202 -0.1035 0.6272 0.0012
-10.000 0.2076 0.11250 0.10928 -0.1048 0.6203 0.0012
-9.750 0.2174 0.10982 0.10658 -0.1062 0.6128 0.0012
-9.500 0.2272 0.10717 0.10389 -0.1075 0.6055 0.0012
-9.250 0.2371 0.10453 0.10123 -0.1089 0.5973 0.0012
-9.000 0.2470 0.10191 0.09857 -0.1103 0.5898 0.0012
-8.750 0.2571 0.09931 0.09595 -0.1116 0.5816 0.0012
-8.500 0.2672 0.09674 0.09335 -0.1130 0.5743 0.0012
-8.250 0.2773 0.09418 0.09076 -0.1144 0.5660 0.0012
-8.000 0.2876 0.09164 0.08819 -0.1158 0.5578 0.0012
-7.750 0.2978 0.08914 0.08565 -0.1172 0.5481 0.0012
-7.500 0.3082 0.08666 0.08313 -0.1187 0.5377 0.0012
-5.750 0.3749 0.06980 0.06602 -0.1271 0.4660 0.0014
-5.500 0.3858 0.06760 0.06379 -0.1289 0.4577 0.0014
-5.250 0.3999 0.06516 0.06132 -0.1315 0.4502 0.0015
-5.000 0.4155 0.06265 0.05878 -0.1345 0.4433 0.0015
-4.750 0.4335 0.06000 0.05612 -0.1381 0.4376 0.0016
-4.500 0.4535 0.05725 0.05333 -0.1422 0.4320 0.0016
-4.250 0.4764 0.05432 0.05038 -0.1470 0.4275 0.0017
-4.000 0.5029 0.05119 0.04722 -0.1527 0.4229 0.0018
-3.750 0.5334 0.04784 0.04383 -0.1592 0.4179 0.0019
-3.500 0.5696 0.04418 0.04010 -0.1671 0.4132 0.0020
-3.250 0.6141 0.03997 0.03582 -0.1768 0.4087 0.0022
-3.000 0.6678 0.03518 0.03089 -0.1882 0.4040 0.0024
-2.750 0.7285 0.03010 0.02558 -0.1995 0.3997 0.0027
-2.500 0.7824 0.02624 0.02145 -0.2073 0.3966 0.0028
-2.250 0.8324 0.02303 0.01795 -0.2134 0.3928 0.0028
-2.000 0.8792 0.02031 0.01489 -0.2182 0.3885 0.0028
-1.750 0.9299 0.01716 0.01127 -0.2238 0.3841 0.0031
-1.500 0.9708 0.01547 0.00925 -0.2265 0.3809 0.0030
-1.000 1.0476 0.01288 0.00607 -0.2306 0.3739 0.0011
-0.750 1.0818 0.01233 0.00531 -0.2321 0.3698 0.0011
-0.500 1.1148 0.01200 0.00482 -0.2334 0.3667 0.0013
-0.250 1.1449 0.01191 0.00460 -0.2342 0.3631 0.0016
0.000 1.1732 0.01193 0.00454 -0.2347 0.3594 0.0049
0.250 1.2013 0.01198 0.00460 -0.2352 0.3502 0.0623
0.500 1.2254 0.01227 0.00473 -0.2350 0.3295 0.0945
0.750 1.2497 0.01255 0.00491 -0.2349 0.3134 0.1197
1.000 1.2732 0.01288 0.00521 -0.2348 0.2922 0.2110
1.250 1.2641 0.01530 0.00682 -0.2289 0.1726 0.2246
1.500 1.2519 0.01742 0.00852 -0.2222 0.0240 0.2353
1.750 1.2732 0.01765 0.00885 -0.2216 0.0191 0.2898
2.000 1.2947 0.01794 0.00922 -0.2210 0.0160 0.3331
2.250 1.3154 0.01827 0.00961 -0.2203 0.0125 0.3558
2.500 1.3355 0.01865 0.01005 -0.2195 0.0073 0.3747
2.750 1.3549 0.01907 0.01052 -0.2186 0.0047 0.3873
3.000 1.3729 0.01957 0.01112 -0.2174 0.0049 0.4039
3.250 1.3911 0.02006 0.01168 -0.2163 0.0021 0.4170
3.500 1.4093 0.02059 0.01245 -0.2154 0.0020 0.5015
4.000 1.4396 0.02204 0.01424 -0.2126 0.0036 0.6258
4.250 1.4530 0.02291 0.01524 -0.2109 0.0034 0.6616
4.500 1.4648 0.02391 0.01649 -0.2092 0.0030 0.7410
4.750 1.4670 0.02500 0.01804 -0.2059 0.0028 1.0000
5.000 1.4680 0.02687 0.02002 -0.2030 0.0027 1.0000
5.250 1.4744 0.02842 0.02164 -0.2008 0.0027 1.0000
5.500 1.4828 0.02985 0.02313 -0.1989 0.0026 1.0000
5.750 1.5002 0.03058 0.02385 -0.1981 0.0024 1.0000
6.000 1.5069 0.03222 0.02555 -0.1962 0.0021 1.0000
6.250 1.5096 0.03426 0.02769 -0.1940 0.0019 1.0000
6.500 1.5103 0.03657 0.03008 -0.1919 0.0018 1.0000
6.750 1.5089 0.03917 0.03277 -0.1898 0.0017 1.0000
7.000 1.5062 0.04208 0.03578 -0.1879 0.0016 1.0000
7.250 1.5016 0.04534 0.03914 -0.1862 0.0015 1.0000
7.500 1.4949 0.04899 0.04290 -0.1846 0.0015 1.0000
7.750 1.4863 0.05305 0.04706 -0.1832 0.0014 1.0000
8.000 1.4762 0.05746 0.05158 -0.1819 0.0014 1.0000
8.250 1.4643 0.06219 0.05643 -0.1808 0.0013 1.0000
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Polar data table (+)
Polar graphs
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