GOE 133 (MVA H.11) AIRFOIL (goe133-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 133 (MVA H.11) AIRFOIL (goe133-il) Reynolds number: 500,000 Max Cl/Cd: 92.96 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe133-il-500000-n5.txt Download as CSV file: xf-goe133-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3517 0.09121 0.08900 -0.0230 1.0000 0.0088
-8.000 -0.3497 0.08783 0.08566 -0.0243 1.0000 0.0086
-7.750 -0.3529 0.08480 0.08267 -0.0246 1.0000 0.0083
-7.500 -0.3433 0.07980 0.07768 -0.0300 0.9940 0.0080
-6.500 -0.2529 0.01824 0.01402 -0.0906 0.9526 0.0091
-6.250 -0.2269 0.01610 0.01144 -0.0908 0.9451 0.0097
-6.000 -0.1997 0.01477 0.00981 -0.0909 0.9383 0.0101
-5.750 -0.1732 0.01349 0.00828 -0.0908 0.9308 0.0107
-5.500 -0.1461 0.01278 0.00743 -0.0906 0.9231 0.0113
-5.250 -0.1191 0.01217 0.00668 -0.0904 0.9146 0.0120
-5.000 -0.0921 0.01160 0.00595 -0.0901 0.9054 0.0130
-4.750 -0.0651 0.01113 0.00534 -0.0897 0.8943 0.0139
-4.500 -0.0380 0.01066 0.00480 -0.0894 0.8825 0.0159
-4.250 -0.0109 0.01033 0.00437 -0.0891 0.8700 0.0177
-4.000 0.0163 0.00999 0.00393 -0.0887 0.8555 0.0199
-3.750 0.0435 0.00985 0.00373 -0.0883 0.8385 0.0232
-3.500 0.0705 0.00973 0.00350 -0.0879 0.8192 0.0265
-3.250 0.0978 0.00974 0.00343 -0.0876 0.7982 0.0298
-3.000 0.1250 0.00972 0.00326 -0.0872 0.7777 0.0324
-2.750 0.1521 0.00964 0.00310 -0.0870 0.7577 0.0352
-2.500 0.1795 0.00964 0.00300 -0.0867 0.7372 0.0377
-2.250 0.2068 0.00964 0.00287 -0.0864 0.7166 0.0402
-2.000 0.2340 0.00968 0.00277 -0.0861 0.6937 0.0417
-1.750 0.2608 0.00944 0.00241 -0.0859 0.6668 0.0445
-1.500 0.2878 0.00942 0.00225 -0.0856 0.6367 0.0467
-1.250 0.3148 0.00941 0.00210 -0.0853 0.6054 0.0484
-1.000 0.3418 0.00943 0.00196 -0.0851 0.5770 0.0503
-0.750 0.3690 0.00946 0.00185 -0.0849 0.5522 0.0521
-0.500 0.3963 0.00950 0.00178 -0.0848 0.5333 0.0535
-0.250 0.4239 0.00949 0.00168 -0.0846 0.5172 0.0571
0.000 0.4514 0.00950 0.00163 -0.0845 0.5023 0.0618
0.500 0.5067 0.00954 0.00160 -0.0844 0.4762 0.0754
0.750 0.5344 0.00953 0.00162 -0.0843 0.4646 0.1042
1.000 0.5620 0.00950 0.00166 -0.0843 0.4531 0.1518
1.250 0.5818 0.00784 0.00187 -0.0833 0.4443 0.8450
2.000 0.6678 0.00794 0.00197 -0.0834 0.4193 1.0000
2.250 0.6953 0.00808 0.00203 -0.0833 0.4107 1.0000
2.500 0.7229 0.00820 0.00211 -0.0832 0.4014 1.0000
2.750 0.7504 0.00834 0.00220 -0.0831 0.3919 1.0000
3.000 0.7776 0.00850 0.00230 -0.0830 0.3798 1.0000
3.250 0.8047 0.00869 0.00241 -0.0828 0.3618 1.0000
3.500 0.8311 0.00894 0.00253 -0.0827 0.3376 1.0000
3.750 0.8571 0.00925 0.00269 -0.0824 0.3045 1.0000
4.000 0.8825 0.00965 0.00291 -0.0821 0.2688 1.0000
4.250 0.9081 0.01002 0.00315 -0.0818 0.2445 1.0000
4.500 0.9339 0.01036 0.00339 -0.0816 0.2267 1.0000
4.750 0.9599 0.01066 0.00364 -0.0813 0.2135 1.0000
5.000 0.9859 0.01095 0.00388 -0.0811 0.2034 1.0000
5.500 1.0380 0.01149 0.00438 -0.0806 0.1864 1.0000
5.750 1.0638 0.01178 0.00464 -0.0804 0.1797 1.0000
6.000 1.0900 0.01201 0.00490 -0.0801 0.1749 1.0000
6.250 1.1159 0.01226 0.00516 -0.0799 0.1694 1.0000
6.500 1.1413 0.01256 0.00547 -0.0796 0.1623 1.0000
6.750 1.1671 0.01281 0.00575 -0.0793 0.1553 1.0000
7.000 1.1922 0.01313 0.00606 -0.0790 0.1466 1.0000
7.250 1.2170 0.01349 0.00639 -0.0786 0.1311 1.0000
7.500 1.2372 0.01437 0.00701 -0.0778 0.0861 1.0000
7.750 1.2602 0.01491 0.00754 -0.0771 0.0779 1.0000
8.000 1.2834 0.01540 0.00805 -0.0766 0.0708 1.0000
8.250 1.3059 0.01595 0.00860 -0.0759 0.0633 1.0000
8.500 1.3288 0.01643 0.00913 -0.0753 0.0579 1.0000
8.750 1.3514 0.01691 0.00963 -0.0746 0.0530 1.0000
9.000 1.3731 0.01747 0.01020 -0.0739 0.0481 1.0000
9.250 1.3954 0.01792 0.01071 -0.0732 0.0445 1.0000
9.500 1.4160 0.01854 0.01131 -0.0723 0.0390 1.0000
9.750 1.4371 0.01907 0.01189 -0.0715 0.0347 1.0000
10.000 1.4565 0.01974 0.01257 -0.0705 0.0286 1.0000
10.500 1.4872 0.02168 0.01444 -0.0674 0.0126 1.0000
10.750 1.5028 0.02254 0.01538 -0.0658 0.0107 1.0000
11.000 1.5162 0.02350 0.01642 -0.0640 0.0094 1.0000
11.250 1.5265 0.02449 0.01750 -0.0617 0.0085 1.0000
11.500 1.5369 0.02542 0.01854 -0.0594 0.0079 1.0000
11.750 1.5456 0.02649 0.01973 -0.0572 0.0073 1.0000
12.000 1.5524 0.02774 0.02107 -0.0549 0.0068 1.0000
12.250 1.5562 0.02928 0.02272 -0.0525 0.0064 1.0000
12.500 1.5615 0.03077 0.02433 -0.0506 0.0061 1.0000
12.750 1.5663 0.03240 0.02607 -0.0489 0.0058 1.0000
13.000 1.5695 0.03427 0.02807 -0.0474 0.0055 1.0000
13.250 1.5711 0.03641 0.03035 -0.0461 0.0053 1.0000
13.500 1.5716 0.03884 0.03290 -0.0452 0.0051 1.0000
13.750 1.5705 0.04160 0.03579 -0.0446 0.0050 1.0000
14.000 1.5676 0.04476 0.03908 -0.0444 0.0048 1.0000
14.250 1.5625 0.04839 0.04287 -0.0446 0.0047 1.0000
14.500 1.5551 0.05251 0.04713 -0.0452 0.0046 1.0000
14.750 1.5447 0.05730 0.05206 -0.0463 0.0045 1.0000
15.000 1.5319 0.06258 0.05750 -0.0477 0.0044 1.0000
15.250 1.5188 0.06809 0.06314 -0.0494 0.0044 1.0000
15.500 1.5066 0.07358 0.06878 -0.0512 0.0044 1.0000
15.750 1.4934 0.07928 0.07462 -0.0531 0.0043 1.0000
16.000 1.4790 0.08530 0.08078 -0.0552 0.0043 1.0000
16.250 1.4637 0.09159 0.08721 -0.0575 0.0043 1.0000
16.500 1.4481 0.09803 0.09379 -0.0599 0.0042 1.0000
16.750 1.4324 0.10467 0.10056 -0.0625 0.0042 1.0000
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Polar data table (+)
Polar graphs
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