GOE 133 (MVA H.11) AIRFOIL (goe133-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 133 (MVA H.11) AIRFOIL (goe133-il) Reynolds number: 1,000,000 Max Cl/Cd: 107.99 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe133-il-1000000-n5.txt Download as CSV file: xf-goe133-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 133 (MVA H.11) 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3778 0.09256 0.09097 -0.0212 1.0000 0.0048
-8.250 -0.4432 0.01878 0.01538 -0.0899 0.9614 0.0054
-8.000 -0.4192 0.01668 0.01303 -0.0901 0.9547 0.0056
-7.750 -0.3940 0.01535 0.01149 -0.0901 0.9483 0.0058
-7.500 -0.3685 0.01437 0.01034 -0.0899 0.9408 0.0060
-7.250 -0.3427 0.01350 0.00931 -0.0897 0.9332 0.0061
-7.000 -0.3168 0.01279 0.00844 -0.0893 0.9238 0.0064
-6.750 -0.2903 0.01212 0.00763 -0.0891 0.9150 0.0067
-6.500 -0.2637 0.01154 0.00691 -0.0888 0.9069 0.0069
-6.250 -0.2365 0.01104 0.00627 -0.0887 0.8975 0.0071
-6.000 -0.2096 0.01056 0.00566 -0.0884 0.8868 0.0074
-5.750 -0.1827 0.01005 0.00503 -0.0882 0.8746 0.0080
-5.500 -0.1555 0.00971 0.00460 -0.0879 0.8612 0.0086
-5.250 -0.1282 0.00942 0.00421 -0.0877 0.8464 0.0092
-5.000 -0.1009 0.00916 0.00382 -0.0874 0.8288 0.0098
-4.750 -0.0736 0.00893 0.00346 -0.0871 0.8076 0.0103
-4.500 -0.0464 0.00867 0.00307 -0.0869 0.7854 0.0115
-4.250 -0.0190 0.00850 0.00279 -0.0867 0.7641 0.0128
-4.000 0.0087 0.00837 0.00253 -0.0865 0.7453 0.0142
-3.750 0.0364 0.00821 0.00231 -0.0864 0.7278 0.0173
-3.500 0.0642 0.00811 0.00216 -0.0863 0.7101 0.0210
-3.250 0.0921 0.00807 0.00204 -0.0862 0.6915 0.0247
-3.000 0.1198 0.00806 0.00196 -0.0860 0.6681 0.0278
-2.750 0.1474 0.00811 0.00191 -0.0859 0.6394 0.0306
-2.500 0.1749 0.00818 0.00183 -0.0857 0.6053 0.0321
-2.250 0.2024 0.00821 0.00172 -0.0856 0.5728 0.0341
-1.750 0.2579 0.00830 0.00164 -0.0854 0.5282 0.0387
-1.500 0.2858 0.00834 0.00159 -0.0854 0.5092 0.0403
-1.250 0.3137 0.00836 0.00153 -0.0853 0.4936 0.0413
-1.000 0.3417 0.00837 0.00147 -0.0853 0.4803 0.0418
-0.750 0.3698 0.00831 0.00134 -0.0853 0.4691 0.0442
-0.250 0.4261 0.00829 0.00125 -0.0852 0.4486 0.0490
0.000 0.4542 0.00831 0.00123 -0.0852 0.4387 0.0511
0.250 0.4821 0.00835 0.00122 -0.0852 0.4278 0.0530
0.500 0.5102 0.00837 0.00120 -0.0852 0.4176 0.0565
0.750 0.5383 0.00838 0.00121 -0.0852 0.4097 0.0631
1.250 0.5944 0.00836 0.00127 -0.0852 0.3945 0.1113
1.500 0.6223 0.00835 0.00132 -0.0852 0.3858 0.1476
1.750 0.6486 0.00715 0.00152 -0.0857 0.3777 0.7295
2.000 0.6731 0.00667 0.00158 -0.0847 0.3676 1.0000
2.250 0.7007 0.00681 0.00164 -0.0846 0.3530 1.0000
2.500 0.7278 0.00703 0.00173 -0.0845 0.3263 1.0000
2.750 0.7539 0.00739 0.00187 -0.0843 0.2842 1.0000
3.000 0.7796 0.00781 0.00207 -0.0840 0.2433 1.0000
3.250 0.8063 0.00808 0.00223 -0.0839 0.2235 1.0000
3.500 0.8334 0.00829 0.00237 -0.0838 0.2114 1.0000
3.750 0.8605 0.00848 0.00251 -0.0837 0.2027 1.0000
4.000 0.8874 0.00870 0.00267 -0.0835 0.1928 1.0000
4.250 0.9145 0.00887 0.00281 -0.0834 0.1855 1.0000
4.500 0.9413 0.00909 0.00298 -0.0833 0.1767 1.0000
4.750 0.9683 0.00928 0.00314 -0.0832 0.1704 1.0000
5.000 0.9952 0.00947 0.00331 -0.0831 0.1654 1.0000
5.250 1.0222 0.00964 0.00348 -0.0830 0.1617 1.0000
5.500 1.0491 0.00981 0.00366 -0.0829 0.1576 1.0000
5.750 1.0756 0.01002 0.00385 -0.0827 0.1522 1.0000
6.000 1.1022 0.01022 0.00404 -0.0826 0.1470 1.0000
6.250 1.1285 0.01045 0.00425 -0.0824 0.1385 1.0000
6.500 1.1523 0.01099 0.00460 -0.0819 0.1024 1.0000
6.750 1.1760 0.01154 0.00504 -0.0814 0.0814 1.0000
7.000 1.2010 0.01191 0.00539 -0.0811 0.0739 1.0000
7.250 1.2265 0.01219 0.00570 -0.0808 0.0696 1.0000
7.500 1.2506 0.01264 0.00611 -0.0803 0.0605 1.0000
7.750 1.2756 0.01295 0.00642 -0.0800 0.0561 1.0000
8.000 1.2996 0.01337 0.00681 -0.0795 0.0496 1.0000
8.250 1.3242 0.01370 0.00716 -0.0791 0.0457 1.0000
8.500 1.3479 0.01412 0.00756 -0.0786 0.0412 1.0000
8.750 1.3718 0.01450 0.00795 -0.0782 0.0377 1.0000
9.000 1.3952 0.01492 0.00837 -0.0776 0.0335 1.0000
9.250 1.4179 0.01539 0.00883 -0.0770 0.0287 1.0000
9.750 1.4580 0.01682 0.01018 -0.0751 0.0115 1.0000
10.000 1.4784 0.01746 0.01084 -0.0741 0.0093 1.0000
10.250 1.4990 0.01803 0.01146 -0.0732 0.0079 1.0000
10.500 1.5184 0.01868 0.01215 -0.0722 0.0068 1.0000
10.750 1.5374 0.01933 0.01284 -0.0711 0.0060 1.0000
11.000 1.5563 0.01994 0.01351 -0.0699 0.0055 1.0000
11.250 1.5738 0.02063 0.01426 -0.0686 0.0051 1.0000
11.500 1.5896 0.02141 0.01510 -0.0671 0.0046 1.0000
11.750 1.6041 0.02221 0.01597 -0.0654 0.0043 1.0000
12.000 1.6164 0.02294 0.01678 -0.0633 0.0041 1.0000
12.250 1.6272 0.02377 0.01769 -0.0610 0.0039 1.0000
12.500 1.6369 0.02469 0.01869 -0.0588 0.0037 1.0000
12.750 1.6456 0.02572 0.01979 -0.0567 0.0036 1.0000
13.000 1.6530 0.02689 0.02103 -0.0545 0.0034 1.0000
13.250 1.6586 0.02825 0.02249 -0.0525 0.0032 1.0000
13.500 1.6615 0.02993 0.02427 -0.0504 0.0030 1.0000
13.750 1.6665 0.03153 0.02597 -0.0488 0.0029 1.0000
14.000 1.6706 0.03331 0.02785 -0.0475 0.0028 1.0000
14.250 1.6734 0.03533 0.02998 -0.0463 0.0028 1.0000
14.500 1.6749 0.03763 0.03238 -0.0454 0.0027 1.0000
14.750 1.6747 0.04025 0.03512 -0.0448 0.0026 1.0000
15.000 1.6731 0.04321 0.03819 -0.0446 0.0025 1.0000
15.250 1.6704 0.04646 0.04156 -0.0447 0.0025 1.0000
15.500 1.6652 0.05016 0.04538 -0.0451 0.0024 1.0000
15.750 1.6589 0.05420 0.04954 -0.0458 0.0024 1.0000
16.000 1.6505 0.05866 0.05413 -0.0468 0.0023 1.0000
16.250 1.6400 0.06357 0.05917 -0.0481 0.0023 1.0000
16.500 1.6277 0.06892 0.06464 -0.0497 0.0023 1.0000
16.750 1.6134 0.07462 0.07049 -0.0515 0.0023 1.0000
17.000 1.5973 0.08069 0.07669 -0.0536 0.0022 1.0000
17.250 1.5801 0.08710 0.08323 -0.0558 0.0022 1.0000
17.500 1.5615 0.09380 0.09006 -0.0582 0.0022 1.0000
17.750 1.5420 0.10084 0.09723 -0.0609 0.0022 1.0000
18.000 1.5219 0.10818 0.10469 -0.0639 0.0022 1.0000
18.250 1.5019 0.11562 0.11226 -0.0670 0.0022 1.0000
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