GOE 143 (MVA H.20) AIRFOIL (goe143-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 143 (MVA H.20) AIRFOIL (goe143-il) Reynolds number: 1,000,000 Max Cl/Cd: 98.18 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe143-il-1000000-n5.txt Download as CSV file: xf-goe143-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 143 (MVA H.20) 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5216 0.09788 0.09628 -0.0042 1.0000 0.0083
-9.750 -0.5205 0.09359 0.09201 -0.0066 1.0000 0.0087
-9.250 -0.6443 0.01741 0.01370 -0.0739 1.0000 0.0112
-9.000 -0.6219 0.01521 0.01125 -0.0740 1.0000 0.0125
-8.750 -0.5978 0.01413 0.01003 -0.0737 1.0000 0.0138
-8.500 -0.5697 0.01337 0.00921 -0.0741 0.9986 0.0159
-8.250 -0.5380 0.01278 0.00852 -0.0751 0.9961 0.0177
-8.000 -0.5059 0.01259 0.00834 -0.0760 0.9928 0.0193
-7.750 -0.4739 0.01252 0.00829 -0.0768 0.9884 0.0208
-7.500 -0.4420 0.01226 0.00797 -0.0776 0.9835 0.0220
-7.250 -0.4105 0.01193 0.00756 -0.0784 0.9753 0.0227
-7.000 -0.3812 0.01169 0.00723 -0.0786 0.9612 0.0232
-6.750 -0.3552 0.01133 0.00677 -0.0780 0.9407 0.0240
-6.500 -0.3297 0.01128 0.00666 -0.0772 0.9178 0.0248
-6.250 -0.3034 0.01128 0.00659 -0.0766 0.8942 0.0254
-6.000 -0.2770 0.01129 0.00651 -0.0761 0.8713 0.0261
-5.750 -0.2499 0.01130 0.00643 -0.0757 0.8514 0.0268
-5.500 -0.2224 0.01127 0.00630 -0.0755 0.8348 0.0276
-5.250 -0.1948 0.01108 0.00600 -0.0753 0.8211 0.0283
-5.000 -0.1670 0.01083 0.00564 -0.0752 0.8090 0.0288
-4.750 -0.1391 0.01050 0.00519 -0.0751 0.7977 0.0291
-4.500 -0.1112 0.01019 0.00476 -0.0750 0.7861 0.0293
-4.250 -0.0831 0.00989 0.00437 -0.0749 0.7746 0.0295
-4.000 -0.0550 0.00963 0.00401 -0.0748 0.7626 0.0296
-3.750 -0.0271 0.00918 0.00346 -0.0748 0.7504 0.0301
-3.500 0.0010 0.00882 0.00299 -0.0748 0.7357 0.0309
-3.250 0.0292 0.00863 0.00274 -0.0747 0.7194 0.0316
-3.000 0.0573 0.00855 0.00259 -0.0746 0.6992 0.0324
-2.750 0.0855 0.00850 0.00244 -0.0746 0.6763 0.0331
-2.500 0.1136 0.00844 0.00227 -0.0745 0.6517 0.0338
-2.250 0.1417 0.00839 0.00212 -0.0744 0.6257 0.0345
-2.000 0.1698 0.00837 0.00197 -0.0744 0.5989 0.0352
-1.750 0.1979 0.00835 0.00185 -0.0743 0.5738 0.0359
-1.500 0.2261 0.00834 0.00174 -0.0743 0.5492 0.0365
-1.250 0.2542 0.00836 0.00165 -0.0743 0.5248 0.0370
-1.000 0.2824 0.00837 0.00158 -0.0743 0.5033 0.0374
-0.750 0.3107 0.00833 0.00145 -0.0743 0.4840 0.0386
-0.500 0.3388 0.00834 0.00137 -0.0743 0.4603 0.0404
-0.250 0.3669 0.00841 0.00135 -0.0743 0.4356 0.0420
0.000 0.3950 0.00848 0.00134 -0.0743 0.4145 0.0436
0.250 0.4231 0.00853 0.00133 -0.0743 0.3985 0.0455
0.500 0.4514 0.00857 0.00133 -0.0742 0.3865 0.0468
0.750 0.4796 0.00862 0.00133 -0.0742 0.3760 0.0476
1.000 0.5078 0.00864 0.00131 -0.0742 0.3634 0.0507
1.250 0.5359 0.00868 0.00133 -0.0742 0.3500 0.0541
1.500 0.5641 0.00873 0.00135 -0.0742 0.3386 0.0572
1.750 0.5920 0.00882 0.00139 -0.0742 0.3233 0.0602
2.000 0.6198 0.00893 0.00146 -0.0742 0.3051 0.0726
2.250 0.6476 0.00902 0.00155 -0.0742 0.2882 0.0959
2.500 0.6754 0.00913 0.00163 -0.0742 0.2739 0.1073
2.750 0.7032 0.00923 0.00171 -0.0741 0.2594 0.1251
3.250 0.7535 0.00779 0.00210 -0.0736 0.2247 1.0000
3.500 0.7805 0.00809 0.00226 -0.0735 0.1997 1.0000
3.750 0.8072 0.00845 0.00246 -0.0734 0.1701 1.0000
4.000 0.8338 0.00881 0.00268 -0.0732 0.1432 1.0000
4.250 0.8607 0.00910 0.00288 -0.0731 0.1273 1.0000
4.500 0.8878 0.00935 0.00308 -0.0730 0.1173 1.0000
4.750 0.9151 0.00955 0.00325 -0.0729 0.1123 1.0000
5.000 0.9419 0.00982 0.00346 -0.0727 0.1040 1.0000
5.250 0.9690 0.01003 0.00366 -0.0726 0.0982 1.0000
5.500 0.9958 0.01027 0.00387 -0.0725 0.0934 1.0000
5.750 1.0227 0.01050 0.00408 -0.0723 0.0889 1.0000
6.000 1.0497 0.01070 0.00428 -0.0722 0.0861 1.0000
6.250 1.0761 0.01098 0.00453 -0.0720 0.0798 1.0000
6.500 1.1026 0.01123 0.00476 -0.0718 0.0748 1.0000
6.750 1.1265 0.01187 0.00520 -0.0714 0.0425 1.0000
7.000 1.1504 0.01253 0.00579 -0.0709 0.0230 1.0000
7.250 1.1759 0.01290 0.00617 -0.0706 0.0185 1.0000
7.500 1.2009 0.01332 0.00659 -0.0702 0.0148 1.0000
7.750 1.2262 0.01368 0.00697 -0.0699 0.0131 1.0000
8.000 1.2511 0.01409 0.00739 -0.0695 0.0116 1.0000
8.250 1.2754 0.01456 0.00788 -0.0690 0.0101 1.0000
8.500 1.3000 0.01494 0.00831 -0.0686 0.0095 1.0000
8.750 1.3244 0.01536 0.00875 -0.0682 0.0088 1.0000
9.000 1.3482 0.01582 0.00923 -0.0677 0.0080 1.0000
9.250 1.3712 0.01637 0.00981 -0.0671 0.0072 1.0000
9.500 1.3943 0.01687 0.01036 -0.0665 0.0068 1.0000
9.750 1.4173 0.01737 0.01092 -0.0659 0.0065 1.0000
10.000 1.4397 0.01790 0.01150 -0.0653 0.0061 1.0000
10.250 1.4616 0.01846 0.01210 -0.0646 0.0058 1.0000
10.500 1.4829 0.01907 0.01275 -0.0638 0.0055 1.0000
10.750 1.5030 0.01977 0.01350 -0.0629 0.0052 1.0000
11.000 1.5215 0.02061 0.01443 -0.0617 0.0049 1.0000
11.250 1.5412 0.02126 0.01514 -0.0607 0.0047 1.0000
11.500 1.5599 0.02195 0.01590 -0.0597 0.0046 1.0000
11.750 1.5775 0.02269 0.01671 -0.0585 0.0044 1.0000
12.000 1.5940 0.02348 0.01757 -0.0572 0.0042 1.0000
12.250 1.6090 0.02433 0.01849 -0.0557 0.0040 1.0000
12.500 1.6221 0.02522 0.01946 -0.0539 0.0039 1.0000
12.750 1.6309 0.02616 0.02049 -0.0515 0.0038 1.0000
13.000 1.6379 0.02725 0.02165 -0.0491 0.0037 1.0000
13.250 1.6432 0.02854 0.02303 -0.0468 0.0036 1.0000
13.500 1.6463 0.03012 0.02470 -0.0447 0.0035 1.0000
13.750 1.6466 0.03209 0.02678 -0.0429 0.0034 1.0000
14.000 1.6431 0.03464 0.02947 -0.0414 0.0033 1.0000
14.250 1.6430 0.03712 0.03206 -0.0406 0.0033 1.0000
14.500 1.6422 0.03986 0.03492 -0.0403 0.0032 1.0000
14.750 1.6396 0.04303 0.03822 -0.0403 0.0032 1.0000
15.000 1.6347 0.04670 0.04202 -0.0408 0.0032 1.0000
15.250 1.6271 0.05103 0.04648 -0.0419 0.0031 1.0000
15.500 1.6167 0.05600 0.05159 -0.0435 0.0031 1.0000
15.750 1.6039 0.06158 0.05732 -0.0456 0.0031 1.0000
16.000 1.5878 0.06782 0.06371 -0.0480 0.0031 1.0000
16.250 1.5685 0.07469 0.07072 -0.0507 0.0031 1.0000
16.500 1.5477 0.08187 0.07805 -0.0536 0.0031 1.0000
16.750 1.5237 0.08970 0.08602 -0.0567 0.0031 1.0000
17.000 1.5008 0.09750 0.09394 -0.0599 0.0031 1.0000
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Polar data table (+)
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