GOE 143 (MVA H.20) AIRFOIL (goe143-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 143 (MVA H.20) AIRFOIL (goe143-il) Reynolds number: 100,000 Max Cl/Cd: 55.39 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe143-il-100000-n5.txt Download as CSV file: xf-goe143-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4260 0.11780 0.11276 -0.0057 1.0000 0.0466
-9.250 -0.4255 0.11540 0.11041 -0.0092 1.0000 0.0471
-9.000 -0.4232 0.11241 0.10748 -0.0121 1.0000 0.0473
-8.750 -0.4201 0.10914 0.10425 -0.0146 1.0000 0.0474
-8.500 -0.4166 0.10572 0.10087 -0.0171 1.0000 0.0475
-8.250 -0.4116 0.10204 0.09724 -0.0199 1.0000 0.0475
-8.000 -0.4038 0.09803 0.09325 -0.0238 1.0000 0.0476
-7.750 -0.3904 0.09300 0.08821 -0.0151 1.0000 0.0505
-7.500 -0.3837 0.09016 0.08540 -0.0156 1.0000 0.0529
-7.250 -0.3771 0.08695 0.08223 -0.0181 1.0000 0.0550
-7.000 -0.3689 0.08349 0.07881 -0.0226 1.0000 0.0576
-6.750 -0.3538 0.07947 0.07475 -0.0344 1.0000 0.0598
-6.500 -0.3395 0.07518 0.07039 -0.0397 1.0000 0.0601
-6.250 -0.3241 0.07090 0.06598 -0.0443 1.0000 0.0603
-6.000 -0.3264 0.06785 0.06319 -0.0368 1.0000 0.0627
-5.750 -0.3163 0.06511 0.06047 -0.0366 1.0000 0.0647
-5.500 -0.2976 0.05992 0.05511 -0.0416 1.0000 0.0580
-5.250 -0.2845 0.05622 0.05135 -0.0428 1.0000 0.0563
-5.000 -0.2637 0.05207 0.04698 -0.0464 1.0000 0.0584
-4.750 -0.2479 0.04861 0.04340 -0.0473 1.0000 0.0576
-4.500 -0.2223 0.04465 0.03923 -0.0501 0.9980 0.0564
-4.250 -0.1746 0.03969 0.03375 -0.0571 0.9909 0.0584
-4.000 -0.1302 0.03555 0.02913 -0.0623 0.9838 0.0587
-3.750 -0.0886 0.03210 0.02523 -0.0664 0.9763 0.0586
-3.500 -0.0487 0.02931 0.02196 -0.0695 0.9686 0.0592
-3.250 -0.0084 0.02702 0.01933 -0.0729 0.9625 0.0620
-3.000 0.0270 0.02526 0.01729 -0.0748 0.9527 0.0628
-2.750 0.0633 0.02355 0.01525 -0.0765 0.9432 0.0631
-2.500 0.1002 0.02211 0.01354 -0.0783 0.9339 0.0639
-2.250 0.1332 0.02096 0.01214 -0.0792 0.9213 0.0649
-2.000 0.1659 0.01994 0.01093 -0.0799 0.9082 0.0662
-1.750 0.1981 0.01918 0.00999 -0.0804 0.8944 0.0695
-1.500 0.2298 0.01847 0.00907 -0.0806 0.8799 0.0726
-1.250 0.2605 0.01774 0.00819 -0.0807 0.8647 0.0739
-1.000 0.2897 0.01699 0.00743 -0.0805 0.8488 0.0758
-0.750 0.3183 0.01645 0.00687 -0.0802 0.8321 0.0781
-0.500 0.3460 0.01601 0.00638 -0.0797 0.8143 0.0811
-0.250 0.3731 0.01572 0.00601 -0.0790 0.7951 0.0861
0.000 0.3996 0.01538 0.00570 -0.0784 0.7750 0.0921
0.250 0.4263 0.01514 0.00537 -0.0777 0.7543 0.0978
0.500 0.4526 0.01490 0.00508 -0.0770 0.7312 0.1039
0.750 0.4792 0.01474 0.00483 -0.0763 0.7076 0.1143
1.000 0.5063 0.01451 0.00460 -0.0758 0.6827 0.1381
1.250 0.5297 0.01237 0.00450 -0.0745 0.6587 1.0000
1.500 0.5562 0.01256 0.00440 -0.0738 0.6340 1.0000
1.750 0.5828 0.01277 0.00438 -0.0732 0.6096 1.0000
2.000 0.6092 0.01301 0.00441 -0.0726 0.5871 1.0000
2.250 0.6357 0.01327 0.00451 -0.0722 0.5659 1.0000
2.500 0.6621 0.01356 0.00462 -0.0717 0.5462 1.0000
2.750 0.6883 0.01385 0.00477 -0.0712 0.5257 1.0000
3.000 0.7143 0.01416 0.00494 -0.0707 0.5043 1.0000
3.250 0.7400 0.01449 0.00511 -0.0702 0.4826 1.0000
3.500 0.7657 0.01481 0.00531 -0.0697 0.4598 1.0000
4.000 0.8169 0.01548 0.00578 -0.0688 0.4195 1.0000
4.250 0.8428 0.01581 0.00607 -0.0684 0.4037 1.0000
4.500 0.8687 0.01614 0.00640 -0.0680 0.3879 1.0000
4.750 0.8944 0.01647 0.00672 -0.0676 0.3718 1.0000
5.000 0.9199 0.01682 0.00707 -0.0672 0.3554 1.0000
5.250 0.9453 0.01718 0.00744 -0.0668 0.3388 1.0000
5.500 0.9704 0.01756 0.00785 -0.0663 0.3210 1.0000
5.750 0.9952 0.01797 0.00827 -0.0658 0.3016 1.0000
6.000 1.0197 0.01841 0.00873 -0.0653 0.2792 1.0000
6.250 1.0436 0.01893 0.00923 -0.0647 0.2552 1.0000
6.500 1.0667 0.01955 0.00982 -0.0641 0.2312 1.0000
6.750 1.0896 0.02022 0.01047 -0.0635 0.2109 1.0000
7.000 1.1121 0.02095 0.01119 -0.0628 0.1959 1.0000
7.250 1.1341 0.02171 0.01193 -0.0620 0.1821 1.0000
7.500 1.1556 0.02248 0.01272 -0.0613 0.1673 1.0000
7.750 1.1767 0.02327 0.01349 -0.0606 0.1522 1.0000
8.000 1.1976 0.02405 0.01429 -0.0599 0.1391 1.0000
8.250 1.2182 0.02485 0.01513 -0.0591 0.1289 1.0000
8.500 1.2387 0.02564 0.01600 -0.0583 0.1172 1.0000
8.750 1.2591 0.02643 0.01690 -0.0575 0.1017 1.0000
9.000 1.2800 0.02721 0.01777 -0.0567 0.0775 1.0000
9.500 1.3006 0.03103 0.02125 -0.0531 0.0332 1.0000
9.750 1.3099 0.03289 0.02328 -0.0512 0.0306 1.0000
10.000 1.3150 0.03498 0.02554 -0.0489 0.0284 1.0000
10.250 1.3226 0.03666 0.02746 -0.0469 0.0269 1.0000
10.500 1.3249 0.03850 0.02951 -0.0444 0.0256 1.0000
10.750 1.3244 0.04061 0.03187 -0.0421 0.0247 1.0000
11.000 1.3222 0.04304 0.03449 -0.0403 0.0240 1.0000
11.250 1.3184 0.04581 0.03745 -0.0389 0.0234 1.0000
11.500 1.3133 0.04895 0.04076 -0.0382 0.0230 1.0000
11.750 1.3072 0.05247 0.04445 -0.0380 0.0225 1.0000
12.000 1.3001 0.05634 0.04847 -0.0383 0.0220 1.0000
12.250 1.2922 0.06052 0.05279 -0.0389 0.0216 1.0000
12.500 1.2842 0.06487 0.05726 -0.0397 0.0211 1.0000
12.750 1.2764 0.06916 0.06163 -0.0400 0.0206 1.0000
13.000 1.2723 0.07328 0.06591 -0.0411 0.0202 1.0000
13.250 1.2676 0.07763 0.07044 -0.0424 0.0199 1.0000
13.500 1.2621 0.08217 0.07517 -0.0438 0.0195 1.0000
13.750 1.2564 0.08680 0.07997 -0.0453 0.0192 1.0000
14.000 1.2502 0.09154 0.08488 -0.0468 0.0190 1.0000
14.250 1.2435 0.09651 0.09001 -0.0485 0.0189 1.0000
14.500 1.2361 0.10177 0.09544 -0.0506 0.0187 1.0000
14.750 1.2278 0.10737 0.10122 -0.0530 0.0186 1.0000
15.000 1.2184 0.11336 0.10739 -0.0558 0.0185 1.0000
15.250 1.2085 0.11972 0.11392 -0.0590 0.0185 1.0000
15.500 1.1976 0.12654 0.12091 -0.0627 0.0185 1.0000
15.750 1.1858 0.13386 0.12839 -0.0668 0.0185 1.0000
16.000 1.1733 0.14171 0.13641 -0.0715 0.0185 1.0000
16.250 1.1602 0.15019 0.14504 -0.0766 0.0186 1.0000
16.500 1.1461 0.15947 0.15445 -0.0824 0.0188 1.0000
16.750 1.1313 0.16960 0.16471 -0.0886 0.0190 1.0000
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