GOE 180 (MVA H.26) AIRFOIL (goe180-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 180 (MVA H.26) AIRFOIL (goe180-il) Reynolds number: 500,000 Max Cl/Cd: 99.2 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe180-il-500000-n5.txt Download as CSV file: xf-goe180-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 180 (MVA H.26) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3742 0.08941 0.08716 -0.0287 1.0000 0.0105
-8.500 -0.3838 0.08507 0.08287 -0.0293 1.0000 0.0108
-8.250 -0.3881 0.08286 0.08071 -0.0285 1.0000 0.0109
-8.000 -0.3772 0.07968 0.07754 -0.0319 0.9965 0.0111
-7.750 -0.3564 0.07606 0.07391 -0.0377 0.9912 0.0115
-7.500 -0.3361 0.07173 0.06957 -0.0444 0.9846 0.0121
-7.250 -0.3176 0.06472 0.06253 -0.0543 0.9730 0.0129
-6.750 -0.2674 0.02263 0.01880 -0.0946 0.9432 0.0182
-6.500 -0.2334 0.02217 0.01828 -0.0964 0.9362 0.0186
-6.250 -0.2000 0.02129 0.01725 -0.0982 0.9272 0.0192
-6.000 -0.1682 0.02024 0.01600 -0.0997 0.9169 0.0201
-5.750 -0.1387 0.01842 0.01379 -0.1006 0.9065 0.0215
-5.500 -0.1106 0.01702 0.01200 -0.1010 0.8959 0.0224
-5.250 -0.0826 0.01653 0.01126 -0.1010 0.8851 0.0230
-5.000 -0.0567 0.01492 0.00943 -0.1012 0.8739 0.0240
-4.750 -0.0298 0.01429 0.00865 -0.1011 0.8617 0.0245
-4.500 -0.0029 0.01370 0.00791 -0.1009 0.8483 0.0251
-4.250 0.0241 0.01319 0.00726 -0.1006 0.8334 0.0258
-4.000 0.0510 0.01275 0.00667 -0.1004 0.8167 0.0266
-3.750 0.0777 0.01228 0.00603 -0.1000 0.7962 0.0272
-3.500 0.1041 0.01186 0.00543 -0.0996 0.7718 0.0276
-3.250 0.1303 0.01152 0.00489 -0.0991 0.7431 0.0280
-3.000 0.1561 0.01127 0.00442 -0.0985 0.7101 0.0284
-2.750 0.1818 0.01109 0.00402 -0.0979 0.6733 0.0287
-2.500 0.2075 0.01100 0.00372 -0.0974 0.6386 0.0291
-2.250 0.2339 0.01093 0.00349 -0.0970 0.6108 0.0295
-2.000 0.2605 0.01073 0.00317 -0.0967 0.5891 0.0298
-1.750 0.2873 0.01045 0.00277 -0.0965 0.5704 0.0304
-1.500 0.3143 0.01027 0.00250 -0.0963 0.5537 0.0311
-1.250 0.3415 0.01015 0.00230 -0.0961 0.5399 0.0318
-1.000 0.3690 0.01007 0.00215 -0.0960 0.5289 0.0326
-0.750 0.3966 0.01001 0.00203 -0.0958 0.5189 0.0333
-0.500 0.4242 0.00996 0.00194 -0.0957 0.5101 0.0341
-0.250 0.4517 0.00995 0.00186 -0.0956 0.5014 0.0349
0.000 0.4795 0.00993 0.00181 -0.0955 0.4934 0.0362
0.500 0.5346 0.00996 0.00175 -0.0953 0.4753 0.0405
0.750 0.5620 0.00992 0.00177 -0.0952 0.4668 0.0637
1.000 0.5896 0.00989 0.00179 -0.0951 0.4586 0.0951
1.250 0.6170 0.00981 0.00185 -0.0951 0.4517 0.1559
1.500 0.6446 0.00966 0.00193 -0.0951 0.4454 0.2503
1.750 0.6716 0.00941 0.00203 -0.0952 0.4387 0.4059
2.250 0.7221 0.00830 0.00222 -0.0940 0.4229 1.0000
2.500 0.7497 0.00840 0.00229 -0.0939 0.4154 1.0000
2.750 0.7768 0.00854 0.00237 -0.0937 0.4076 1.0000
3.000 0.8042 0.00866 0.00246 -0.0936 0.3992 1.0000
3.250 0.8313 0.00880 0.00256 -0.0935 0.3913 1.0000
3.500 0.8584 0.00893 0.00267 -0.0933 0.3813 1.0000
3.750 0.8854 0.00908 0.00278 -0.0931 0.3707 1.0000
4.000 0.9121 0.00925 0.00291 -0.0929 0.3586 1.0000
4.250 0.9384 0.00946 0.00305 -0.0927 0.3395 1.0000
4.500 0.9639 0.00975 0.00322 -0.0923 0.3114 1.0000
4.750 0.9884 0.01016 0.00346 -0.0918 0.2785 1.0000
5.000 1.0132 0.01054 0.00374 -0.0914 0.2570 1.0000
5.250 1.0385 0.01086 0.00400 -0.0910 0.2440 1.0000
5.500 1.0640 0.01115 0.00426 -0.0907 0.2343 1.0000
5.750 1.0896 0.01142 0.00453 -0.0903 0.2269 1.0000
6.000 1.1152 0.01169 0.00480 -0.0900 0.2199 1.0000
6.250 1.1404 0.01198 0.00509 -0.0896 0.2125 1.0000
6.500 1.1652 0.01231 0.00541 -0.0892 0.2023 1.0000
6.750 1.1901 0.01261 0.00571 -0.0888 0.1908 1.0000
7.000 1.2139 0.01304 0.00605 -0.0882 0.1711 1.0000
7.250 1.2366 0.01356 0.00643 -0.0875 0.1441 1.0000
7.500 1.2587 0.01412 0.00690 -0.0868 0.1256 1.0000
7.750 1.2813 0.01461 0.00736 -0.0860 0.1145 1.0000
8.000 1.3031 0.01516 0.00787 -0.0852 0.1028 1.0000
8.500 1.3374 0.01710 0.00942 -0.0823 0.0371 1.0000
8.750 1.3551 0.01796 0.01025 -0.0809 0.0232 1.0000
9.000 1.3741 0.01866 0.01095 -0.0796 0.0179 1.0000
9.250 1.3930 0.01934 0.01167 -0.0784 0.0152 1.0000
9.500 1.4121 0.01996 0.01236 -0.0771 0.0137 1.0000
9.750 1.4295 0.02068 0.01313 -0.0757 0.0124 1.0000
10.000 1.4447 0.02153 0.01406 -0.0739 0.0111 1.0000
10.250 1.4611 0.02221 0.01483 -0.0723 0.0105 1.0000
10.500 1.4745 0.02297 0.01567 -0.0703 0.0099 1.0000
10.750 1.4859 0.02380 0.01658 -0.0679 0.0094 1.0000
11.000 1.4958 0.02474 0.01760 -0.0655 0.0089 1.0000
11.250 1.5034 0.02586 0.01880 -0.0630 0.0085 1.0000
11.500 1.5071 0.02730 0.02036 -0.0602 0.0081 1.0000
11.750 1.5152 0.02849 0.02165 -0.0582 0.0078 1.0000
12.000 1.5220 0.02984 0.02311 -0.0562 0.0075 1.0000
12.250 1.5274 0.03138 0.02476 -0.0544 0.0072 1.0000
12.500 1.5320 0.03309 0.02658 -0.0528 0.0069 1.0000
12.750 1.5353 0.03501 0.02860 -0.0514 0.0067 1.0000
13.000 1.5374 0.03719 0.03089 -0.0503 0.0065 1.0000
13.250 1.5378 0.03968 0.03349 -0.0494 0.0063 1.0000
13.500 1.5364 0.04253 0.03645 -0.0488 0.0062 1.0000
13.750 1.5326 0.04587 0.03992 -0.0487 0.0060 1.0000
14.000 1.5263 0.04971 0.04390 -0.0489 0.0059 1.0000
14.250 1.5170 0.05414 0.04846 -0.0495 0.0058 1.0000
14.500 1.5078 0.05872 0.05317 -0.0504 0.0057 1.0000
14.750 1.5002 0.06314 0.05772 -0.0513 0.0057 1.0000
15.000 1.4919 0.06775 0.06247 -0.0523 0.0056 1.0000
15.250 1.4825 0.07260 0.06745 -0.0535 0.0056 1.0000
15.500 1.4721 0.07762 0.07261 -0.0548 0.0055 1.0000
15.750 1.4612 0.08284 0.07795 -0.0563 0.0055 1.0000
16.000 1.4504 0.08815 0.08338 -0.0579 0.0054 1.0000
16.250 1.4390 0.09358 0.08894 -0.0596 0.0054 1.0000
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Polar data table (+)
Polar graphs
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