GOE 133 (MVA H.11) AIRFOIL (goe133-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 133 (MVA H.11) AIRFOIL (goe133-il) Reynolds number: 50,000 Max Cl/Cd: 40.85 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe133-il-50000-n5.txt Download as CSV file: xf-goe133-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3421 0.09722 0.09065 -0.0237 1.0000 0.0884
-7.250 -0.3407 0.09462 0.08815 -0.0245 1.0000 0.0909
-7.000 -0.3407 0.09231 0.08594 -0.0267 1.0000 0.0939
-6.750 -0.3419 0.09074 0.08444 -0.0327 1.0000 0.0961
-6.500 -0.3372 0.08843 0.08213 -0.0377 1.0000 0.0967
-6.250 -0.3319 0.08355 0.07739 -0.0330 1.0000 0.0982
-6.000 -0.3263 0.08029 0.07420 -0.0305 1.0000 0.1010
-5.750 -0.3204 0.07753 0.07148 -0.0308 1.0000 0.1057
-5.250 -0.3048 0.07138 0.06536 -0.0345 1.0000 0.1154
-4.750 -0.2613 0.06098 0.05450 -0.0435 1.0000 0.0664
-4.500 -0.2481 0.05753 0.05103 -0.0437 1.0000 0.0635
-4.250 -0.2288 0.05375 0.04708 -0.0457 1.0000 0.0610
-4.000 -0.2067 0.05017 0.04328 -0.0478 1.0000 0.0608
-3.750 -0.1830 0.04690 0.03975 -0.0498 1.0000 0.0629
-3.500 -0.1528 0.04334 0.03580 -0.0526 0.9986 0.0639
-3.250 -0.1045 0.03907 0.03093 -0.0583 0.9915 0.0647
-3.000 -0.0582 0.03572 0.02700 -0.0632 0.9840 0.0705
-2.750 -0.0132 0.03300 0.02378 -0.0672 0.9763 0.0742
-2.500 0.0318 0.03076 0.02075 -0.0705 0.9673 0.0824
-2.250 0.0719 0.02888 0.01868 -0.0733 0.9576 0.0874
-2.000 0.1153 0.02753 0.01673 -0.0760 0.9481 0.0966
-1.750 0.1558 0.02610 0.01515 -0.0784 0.9380 0.1012
-1.500 0.1942 0.02523 0.01399 -0.0801 0.9260 0.1108
-1.250 0.2331 0.02431 0.01294 -0.0819 0.9144 0.1184
-1.000 0.2727 0.02355 0.01195 -0.0836 0.9028 0.1261
-0.750 0.3099 0.02288 0.01122 -0.0850 0.8900 0.1411
-0.500 0.3453 0.02224 0.01056 -0.0861 0.8759 0.1575
-0.250 0.3793 0.02156 0.00997 -0.0870 0.8610 0.1855
0.000 0.4077 0.01878 0.00952 -0.0864 0.8466 1.0000
0.250 0.4392 0.01883 0.00912 -0.0864 0.8293 1.0000
0.500 0.4704 0.01888 0.00887 -0.0865 0.8123 1.0000
0.750 0.5013 0.01894 0.00868 -0.0865 0.7954 1.0000
1.000 0.5316 0.01901 0.00854 -0.0864 0.7788 1.0000
1.250 0.5613 0.01911 0.00846 -0.0862 0.7624 1.0000
1.500 0.5903 0.01924 0.00843 -0.0859 0.7462 1.0000
1.750 0.6187 0.01942 0.00846 -0.0856 0.7302 1.0000
2.000 0.6466 0.01963 0.00854 -0.0851 0.7144 1.0000
2.250 0.6735 0.01987 0.00866 -0.0846 0.6968 1.0000
2.500 0.6992 0.02009 0.00877 -0.0837 0.6762 1.0000
2.750 0.7251 0.02025 0.00880 -0.0827 0.6552 1.0000
3.000 0.7498 0.02048 0.00892 -0.0816 0.6332 1.0000
3.250 0.7750 0.02074 0.00908 -0.0807 0.6132 1.0000
3.500 0.8006 0.02104 0.00933 -0.0800 0.5963 1.0000
3.750 0.8263 0.02137 0.00961 -0.0793 0.5802 1.0000
4.000 0.8518 0.02173 0.00993 -0.0786 0.5645 1.0000
4.250 0.8772 0.02211 0.01032 -0.0780 0.5489 1.0000
4.500 0.9023 0.02253 0.01073 -0.0773 0.5332 1.0000
4.750 0.9270 0.02298 0.01120 -0.0766 0.5171 1.0000
5.000 0.9515 0.02345 0.01175 -0.0759 0.5008 1.0000
5.250 0.9757 0.02396 0.01232 -0.0752 0.4846 1.0000
5.500 0.9997 0.02449 0.01293 -0.0745 0.4684 1.0000
5.750 1.0233 0.02505 0.01360 -0.0737 0.4516 1.0000
6.000 1.0465 0.02563 0.01428 -0.0729 0.4347 1.0000
6.250 1.0696 0.02624 0.01498 -0.0721 0.4180 1.0000
6.500 1.0924 0.02689 0.01573 -0.0712 0.4018 1.0000
6.750 1.1148 0.02754 0.01652 -0.0704 0.3858 1.0000
7.000 1.1365 0.02819 0.01726 -0.0694 0.3695 1.0000
7.250 1.1573 0.02880 0.01795 -0.0682 0.3528 1.0000
7.500 1.1769 0.02947 0.01874 -0.0670 0.3356 1.0000
7.750 1.1960 0.03017 0.01957 -0.0658 0.3186 1.0000
8.000 1.2145 0.03091 0.02048 -0.0645 0.3024 1.0000
8.250 1.2321 0.03169 0.02137 -0.0631 0.2861 1.0000
8.500 1.2482 0.03254 0.02229 -0.0616 0.2692 1.0000
8.750 1.2639 0.03351 0.02336 -0.0601 0.2536 1.0000
9.000 1.2780 0.03459 0.02453 -0.0585 0.2376 1.0000
9.250 1.2901 0.03583 0.02591 -0.0567 0.2209 1.0000
9.500 1.3004 0.03724 0.02749 -0.0548 0.2038 1.0000
9.750 1.3085 0.03880 0.02921 -0.0527 0.1868 1.0000
10.000 1.3141 0.04050 0.03105 -0.0505 0.1705 1.0000
10.250 1.3175 0.04230 0.03296 -0.0481 0.1565 1.0000
10.500 1.3207 0.04421 0.03498 -0.0458 0.1454 1.0000
10.750 1.3236 0.04623 0.03712 -0.0437 0.1360 1.0000
11.000 1.3253 0.04851 0.03960 -0.0418 0.1268 1.0000
11.250 1.3246 0.05087 0.04208 -0.0402 0.1192 1.0000
11.500 1.3228 0.05343 0.04480 -0.0389 0.1123 1.0000
11.750 1.3211 0.05634 0.04786 -0.0379 0.1062 1.0000
12.000 1.3161 0.05936 0.05091 -0.0373 0.1002 1.0000
12.250 1.3091 0.06307 0.05477 -0.0371 0.0941 1.0000
12.500 1.3022 0.06667 0.05834 -0.0372 0.0883 1.0000
12.750 1.2942 0.07097 0.06282 -0.0376 0.0832 1.0000
13.000 1.2859 0.07543 0.06745 -0.0383 0.0784 1.0000
13.250 1.2827 0.07896 0.07086 -0.0381 0.0731 1.0000
13.500 1.2686 0.08483 0.07712 -0.0399 0.0704 1.0000
13.750 1.2549 0.09082 0.08339 -0.0420 0.0677 1.0000
14.000 1.2421 0.09671 0.08949 -0.0441 0.0650 1.0000
14.250 1.2435 0.09955 0.09213 -0.0437 0.0601 1.0000
14.500 1.2252 0.10696 0.09985 -0.0472 0.0593 1.0000
14.750 1.2055 0.11509 0.10825 -0.0514 0.0587 1.0000
15.000 1.1841 0.12415 0.11754 -0.0564 0.0585 1.0000
15.250 1.1611 0.13431 0.12787 -0.0623 0.0587 1.0000
15.500 1.1364 0.14583 0.13949 -0.0690 0.0592 1.0000
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Polar data table (+)
Polar graphs
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