GOE 311 (MVA H.43) AIRFOIL (goe311-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 311 (MVA H.43) AIRFOIL (goe311-il) Reynolds number: 1,000,000 Max Cl/Cd: 97.81 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe311-il-1000000-n5.txt Download as CSV file: xf-goe311-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 311 (MVA H.43) 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 -0.3932 0.07664 0.07425 -0.0340 0.7234 0.0047
-8.500 -0.4037 0.06166 0.05910 -0.0510 0.7188 0.0047
-8.250 -0.3932 0.05080 0.04800 -0.0630 0.7121 0.0048
-8.000 -0.3780 0.03944 0.03625 -0.0733 0.7058 0.0049
-7.750 -0.3588 0.03032 0.02665 -0.0797 0.6995 0.0049
-7.500 -0.3375 0.02365 0.01950 -0.0830 0.6930 0.0050
-7.250 -0.3142 0.01906 0.01449 -0.0846 0.6848 0.0051
-7.000 -0.2890 0.01616 0.01128 -0.0854 0.6753 0.0052
-6.750 -0.2626 0.01456 0.00940 -0.0857 0.6635 0.0055
-6.500 -0.2353 0.01367 0.00832 -0.0859 0.6481 0.0058
-6.250 -0.2078 0.01306 0.00752 -0.0860 0.6255 0.0061
-6.000 -0.1802 0.01260 0.00684 -0.0860 0.5922 0.0064
-5.750 -0.1524 0.01221 0.00622 -0.0861 0.5659 0.0067
-5.250 -0.0962 0.01153 0.00524 -0.0863 0.5415 0.0075
-5.000 -0.0680 0.01116 0.00474 -0.0863 0.5339 0.0080
-4.750 -0.0397 0.01078 0.00427 -0.0864 0.5281 0.0090
-4.500 -0.0114 0.01051 0.00391 -0.0865 0.5227 0.0101
-4.250 0.0171 0.01030 0.00360 -0.0865 0.5184 0.0109
-4.000 0.0457 0.01006 0.00329 -0.0866 0.5152 0.0127
-3.750 0.0741 0.00979 0.00297 -0.0866 0.5119 0.0159
-3.500 0.1025 0.00962 0.00291 -0.0867 0.5089 0.0324
-3.250 0.1312 0.00967 0.00291 -0.0868 0.5058 0.0360
-3.000 0.1598 0.00959 0.00281 -0.0869 0.5031 0.0376
-2.750 0.1885 0.00953 0.00274 -0.0870 0.5007 0.0391
-2.500 0.2172 0.00950 0.00269 -0.0871 0.4983 0.0407
-2.250 0.2458 0.00944 0.00261 -0.0872 0.4960 0.0419
-2.000 0.2744 0.00942 0.00256 -0.0873 0.4936 0.0432
-1.750 0.3030 0.00940 0.00251 -0.0874 0.4911 0.0440
-1.500 0.3315 0.00932 0.00239 -0.0875 0.4888 0.0442
-1.250 0.3601 0.00922 0.00228 -0.0876 0.4872 0.0444
-1.000 0.3887 0.00914 0.00217 -0.0877 0.4852 0.0445
-0.750 0.4172 0.00906 0.00208 -0.0878 0.4823 0.0447
-0.500 0.4456 0.00898 0.00197 -0.0879 0.4784 0.0451
-0.250 0.4739 0.00892 0.00185 -0.0880 0.4739 0.0462
0.000 0.5025 0.00883 0.00177 -0.0881 0.4710 0.0476
0.250 0.5310 0.00878 0.00171 -0.0882 0.4679 0.0492
0.500 0.5595 0.00875 0.00167 -0.0883 0.4639 0.0506
0.750 0.5878 0.00875 0.00164 -0.0884 0.4599 0.0519
1.000 0.6163 0.00873 0.00162 -0.0886 0.4566 0.0532
1.250 0.6448 0.00872 0.00161 -0.0887 0.4512 0.0545
1.500 0.6730 0.00875 0.00161 -0.0888 0.4443 0.0558
1.750 0.7014 0.00874 0.00162 -0.0890 0.4390 0.0624
2.000 0.7295 0.00869 0.00166 -0.0891 0.4324 0.0991
2.250 0.7577 0.00872 0.00171 -0.0892 0.4245 0.1104
2.500 0.7857 0.00879 0.00176 -0.0894 0.4143 0.1176
2.750 0.8138 0.00885 0.00182 -0.0895 0.4045 0.1223
3.000 0.8417 0.00893 0.00190 -0.0896 0.3939 0.1292
3.250 0.8693 0.00905 0.00199 -0.0897 0.3797 0.1337
3.500 0.8965 0.00922 0.00210 -0.0897 0.3616 0.1388
3.750 0.9232 0.00945 0.00226 -0.0897 0.3402 0.1431
4.000 0.9497 0.00971 0.00244 -0.0897 0.3175 0.1474
4.250 0.9759 0.01001 0.00265 -0.0896 0.2947 0.1520
4.500 1.0018 0.01032 0.00288 -0.0895 0.2707 0.1596
4.750 1.0275 0.01064 0.00314 -0.0894 0.2469 0.1714
5.000 1.0529 0.01098 0.00342 -0.0892 0.2234 0.1911
5.250 1.0783 0.01129 0.00372 -0.0891 0.2022 0.2367
5.500 1.1016 0.01185 0.00416 -0.0887 0.1666 0.2804
5.750 1.1233 0.01254 0.00468 -0.0881 0.1190 0.3285
6.000 1.1412 0.01202 0.00528 -0.0867 0.0844 0.9951
6.250 1.1667 0.01233 0.00557 -0.0866 0.0775 1.0000
6.500 1.1919 0.01261 0.00586 -0.0863 0.0738 1.0000
6.750 1.2161 0.01298 0.00621 -0.0860 0.0673 1.0000
7.000 1.2409 0.01327 0.00650 -0.0857 0.0621 1.0000
7.250 1.2580 0.01430 0.00728 -0.0843 0.0180 1.0000
7.500 1.2811 0.01470 0.00769 -0.0838 0.0127 1.0000
7.750 1.3039 0.01512 0.00813 -0.0832 0.0107 1.0000
8.000 1.3256 0.01560 0.00864 -0.0824 0.0087 1.0000
8.250 1.3477 0.01601 0.00908 -0.0818 0.0081 1.0000
8.500 1.3690 0.01647 0.00956 -0.0810 0.0072 1.0000
8.750 1.3888 0.01701 0.01011 -0.0800 0.0064 1.0000
9.000 1.4080 0.01756 0.01070 -0.0789 0.0058 1.0000
9.250 1.4270 0.01808 0.01128 -0.0778 0.0054 1.0000
9.500 1.4446 0.01865 0.01189 -0.0765 0.0050 1.0000
9.750 1.4594 0.01925 0.01253 -0.0747 0.0047 1.0000
10.000 1.4713 0.01997 0.01329 -0.0726 0.0044 1.0000
10.250 1.4808 0.02091 0.01429 -0.0702 0.0041 1.0000
10.500 1.4920 0.02179 0.01524 -0.0683 0.0039 1.0000
10.750 1.5035 0.02272 0.01623 -0.0666 0.0038 1.0000
11.000 1.5142 0.02375 0.01732 -0.0650 0.0036 1.0000
11.250 1.5244 0.02487 0.01850 -0.0634 0.0034 1.0000
11.500 1.5339 0.02609 0.01980 -0.0620 0.0032 1.0000
11.750 1.5424 0.02747 0.02124 -0.0607 0.0031 1.0000
12.000 1.5503 0.02897 0.02280 -0.0595 0.0029 1.0000
12.250 1.5563 0.03074 0.02465 -0.0583 0.0028 1.0000
12.500 1.5600 0.03282 0.02681 -0.0573 0.0027 1.0000
12.750 1.5602 0.03537 0.02946 -0.0563 0.0026 1.0000
13.000 1.5611 0.03794 0.03212 -0.0556 0.0026 1.0000
13.250 1.5630 0.04045 0.03473 -0.0550 0.0025 1.0000
13.500 1.5636 0.04315 0.03752 -0.0545 0.0025 1.0000
13.750 1.5626 0.04610 0.04057 -0.0541 0.0024 1.0000
14.000 1.5607 0.04920 0.04378 -0.0538 0.0024 1.0000
14.250 1.5583 0.05247 0.04715 -0.0537 0.0023 1.0000
14.500 1.5549 0.05599 0.05078 -0.0538 0.0023 1.0000
14.750 1.5507 0.05966 0.05455 -0.0539 0.0022 1.0000
15.000 1.5458 0.06350 0.05849 -0.0542 0.0022 1.0000
15.250 1.5410 0.06736 0.06245 -0.0545 0.0021 1.0000
15.500 1.5353 0.07141 0.06660 -0.0550 0.0021 1.0000
15.750 1.5291 0.07552 0.07080 -0.0554 0.0021 1.0000
16.000 1.5225 0.07977 0.07515 -0.0560 0.0020 1.0000
16.250 1.5156 0.08412 0.07960 -0.0567 0.0020 1.0000
16.500 1.5084 0.08857 0.08414 -0.0575 0.0020 1.0000
16.750 1.5008 0.09310 0.08878 -0.0584 0.0020 1.0000
17.000 1.4939 0.09762 0.09339 -0.0594 0.0019 1.0000
17.250 1.4865 0.10231 0.09817 -0.0605 0.0019 1.0000
17.500 1.4791 0.10706 0.10303 -0.0617 0.0019 1.0000
17.750 1.4711 0.11194 0.10800 -0.0631 0.0018 1.0000
18.000 1.4643 0.11671 0.11287 -0.0645 0.0018 1.0000
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