GOE 629 AIRFOIL (goe629-il) Xfoil prediction polar at RE=100,000 Ncrit=5
Details | Polar file |
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Airfoil: GOE 629 AIRFOIL (goe629-il) Reynolds number: 100,000 Max Cl/Cd: 50.27 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe629-il-100000-n5.txt Download as CSV file: xf-goe629-il-100000-n5.csv |
XFOIL Version 6.96 Calculated polar for: GOE 629 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 ------ -------- --------- --------- -------- -------- -------- -11.250 -0.7494 0.05319 0.04728 -0.0735 1.0000 0.0863 -11.000 -0.8020 0.04946 0.04340 -0.0675 1.0000 0.0864 -10.750 -0.8293 0.04651 0.04025 -0.0630 1.0000 0.0873 -10.500 -0.8484 0.04380 0.03726 -0.0588 1.0000 0.0886 -10.250 -0.8637 0.04100 0.03408 -0.0548 1.0000 0.0903 -10.000 -0.8702 0.03865 0.03136 -0.0513 1.0000 0.0918 -9.750 -0.8578 0.03808 0.03084 -0.0493 1.0000 0.0932 -9.500 -0.8470 0.03740 0.03013 -0.0471 1.0000 0.0947 -9.250 -0.8228 0.03627 0.02884 -0.0478 0.9964 0.0969 -9.000 -0.7985 0.03466 0.02692 -0.0488 0.9920 0.0997 -8.750 -0.7764 0.03273 0.02449 -0.0494 0.9868 0.1027 -8.500 -0.7469 0.03181 0.02351 -0.0506 0.9831 0.1048 -8.250 -0.7198 0.03116 0.02282 -0.0511 0.9783 0.1069 -8.000 -0.6914 0.03038 0.02189 -0.0520 0.9737 0.1098 -7.750 -0.6612 0.02933 0.02056 -0.0532 0.9699 0.1129 -7.500 -0.6378 0.02824 0.01913 -0.0530 0.9637 0.1157 -7.250 -0.6063 0.02766 0.01860 -0.0542 0.9593 0.1182 -7.000 -0.5748 0.02711 0.01799 -0.0553 0.9546 0.1213 -6.750 -0.5467 0.02641 0.01713 -0.0556 0.9476 0.1246 -6.500 -0.5112 0.02559 0.01603 -0.0574 0.9429 0.1287 -6.250 -0.4840 0.02502 0.01548 -0.0575 0.9357 0.1317 -6.000 -0.4527 0.02452 0.01494 -0.0583 0.9299 0.1356 -5.500 -0.3933 0.02339 0.01355 -0.0592 0.9187 0.1444 -5.250 -0.3623 0.02291 0.01311 -0.0600 0.9133 0.1490 -5.000 -0.3263 0.02242 0.01255 -0.0616 0.9098 0.1554 -4.750 -0.3030 0.02201 0.01206 -0.0608 0.9019 0.1607 -4.500 -0.2716 0.02153 0.01163 -0.0615 0.8967 0.1663 -4.250 -0.2347 0.02108 0.01111 -0.0632 0.8932 0.1742 -4.000 -0.2121 0.02074 0.01079 -0.0622 0.8848 0.1805 -3.750 -0.1792 0.02035 0.01041 -0.0631 0.8795 0.1888 -3.500 -0.1419 0.01990 0.00997 -0.0649 0.8760 0.1971 -3.250 -0.1207 0.01967 0.00975 -0.0635 0.8665 0.2045 -3.000 -0.0870 0.01928 0.00940 -0.0645 0.8615 0.2141 -2.750 -0.0585 0.01901 0.00912 -0.0645 0.8544 0.2242 -2.500 -0.0302 0.01869 0.00888 -0.0644 0.8469 0.2346 -2.250 0.0058 0.01830 0.00854 -0.0658 0.8424 0.2486 -2.000 0.0275 0.01814 0.00843 -0.0645 0.8322 0.2624 -1.750 0.0613 0.01776 0.00816 -0.0654 0.8267 0.2821 -1.500 0.0852 0.01753 0.00803 -0.0645 0.8169 0.3018 -1.250 0.1177 0.01716 0.00777 -0.0651 0.8102 0.3279 -1.000 0.1425 0.01692 0.00767 -0.0643 0.8007 0.3580 -0.750 0.1737 0.01655 0.00748 -0.0647 0.7934 0.4010 -0.500 0.1986 0.01628 0.00742 -0.0639 0.7834 0.4503 -0.250 0.2304 0.01586 0.00725 -0.0643 0.7756 0.5166 0.000 0.2543 0.01552 0.00724 -0.0631 0.7640 0.5985 0.250 0.2859 0.01504 0.00721 -0.0629 0.7530 0.7200 0.500 0.3434 0.01476 0.00720 -0.0675 0.7407 0.8443 0.750 0.3990 0.01476 0.00720 -0.0724 0.7266 0.9080 1.000 0.4482 0.01481 0.00720 -0.0762 0.7146 0.9446 1.250 0.4966 0.01484 0.00715 -0.0800 0.7030 0.9717 1.500 0.5587 0.01486 0.00708 -0.0868 0.6903 0.9982 1.750 0.5826 0.01493 0.00709 -0.0861 0.6772 1.0000 2.000 0.6038 0.01502 0.00710 -0.0847 0.6651 1.0000 2.250 0.6266 0.01510 0.00709 -0.0836 0.6538 1.0000 2.500 0.6470 0.01522 0.00717 -0.0820 0.6413 1.0000 2.750 0.6676 0.01537 0.00726 -0.0805 0.6292 1.0000 3.000 0.6898 0.01551 0.00734 -0.0792 0.6180 1.0000 3.250 0.7113 0.01567 0.00745 -0.0779 0.6062 1.0000 3.500 0.7316 0.01587 0.00761 -0.0763 0.5939 1.0000 3.750 0.7531 0.01606 0.00776 -0.0749 0.5823 1.0000 4.000 0.7751 0.01626 0.00790 -0.0736 0.5709 1.0000 4.250 0.7946 0.01649 0.00812 -0.0719 0.5579 1.0000 4.500 0.8143 0.01672 0.00833 -0.0701 0.5437 1.0000 4.750 0.8333 0.01696 0.00851 -0.0683 0.5281 1.0000 5.000 0.8516 0.01721 0.00871 -0.0662 0.5116 1.0000 5.250 0.8700 0.01747 0.00894 -0.0643 0.4961 1.0000 5.500 0.8882 0.01775 0.00918 -0.0623 0.4810 1.0000 5.750 0.9050 0.01803 0.00944 -0.0601 0.4642 1.0000 6.000 0.9209 0.01832 0.00972 -0.0578 0.4466 1.0000 6.250 0.9364 0.01863 0.01001 -0.0553 0.4281 1.0000 6.500 0.9517 0.01896 0.01031 -0.0529 0.4099 1.0000 6.750 0.9671 0.01932 0.01064 -0.0506 0.3928 1.0000 7.000 0.9823 0.01971 0.01100 -0.0483 0.3766 1.0000 7.250 0.9969 0.02013 0.01138 -0.0459 0.3610 1.0000 7.500 1.0108 0.02060 0.01180 -0.0434 0.3454 1.0000 7.750 1.0236 0.02111 0.01226 -0.0408 0.3296 1.0000 8.000 1.0338 0.02166 0.01277 -0.0378 0.3125 1.0000 8.250 1.0429 0.02224 0.01330 -0.0346 0.2952 1.0000 8.500 1.0518 0.02285 0.01388 -0.0316 0.2775 1.0000 8.750 1.0600 0.02352 0.01451 -0.0286 0.2584 1.0000 9.000 1.0680 0.02424 0.01520 -0.0257 0.2396 1.0000 9.250 1.0748 0.02507 0.01596 -0.0228 0.2201 1.0000 9.500 1.0819 0.02596 0.01680 -0.0201 0.2006 1.0000 9.750 1.0881 0.02696 0.01773 -0.0174 0.1837 1.0000 10.000 1.0942 0.02804 0.01875 -0.0149 0.1698 1.0000 10.250 1.1001 0.02919 0.01987 -0.0125 0.1583 1.0000 10.500 1.1059 0.03042 0.02109 -0.0103 0.1475 1.0000 10.750 1.1129 0.03164 0.02234 -0.0083 0.1372 1.0000 11.000 1.1181 0.03301 0.02373 -0.0064 0.1277 1.0000 11.250 1.1218 0.03453 0.02525 -0.0045 0.1187 1.0000 11.500 1.1274 0.03601 0.02679 -0.0028 0.1099 1.0000 11.750 1.1300 0.03775 0.02855 -0.0012 0.1025 1.0000 12.000 1.1326 0.03958 0.03043 0.0003 0.0955 1.0000 12.250 1.1340 0.04157 0.03246 0.0016 0.0895 1.0000 12.500 1.1347 0.04372 0.03465 0.0028 0.0840 1.0000 12.750 1.1345 0.04602 0.03698 0.0039 0.0796 1.0000 13.000 1.1361 0.04826 0.03932 0.0047 0.0753 1.0000 13.250 1.1349 0.05082 0.04190 0.0054 0.0720 1.0000 13.500 1.1359 0.05326 0.04442 0.0059 0.0688 1.0000 13.750 1.1377 0.05570 0.04697 0.0064 0.0660 1.0000 14.000 1.1384 0.05831 0.04964 0.0067 0.0638 1.0000 14.250 1.1386 0.06101 0.05237 0.0068 0.0622 1.0000 14.500 1.1415 0.06351 0.05496 0.0071 0.0604 1.0000 14.750 1.1444 0.06607 0.05765 0.0072 0.0587 1.0000 15.000 1.1463 0.06881 0.06048 0.0071 0.0570 1.0000 15.250 1.1473 0.07168 0.06342 0.0068 0.0556 1.0000 15.500 1.1483 0.07455 0.06634 0.0065 0.0544 1.0000 15.750 1.1502 0.07741 0.06928 0.0063 0.0532 1.0000 16.000 1.1508 0.08058 0.07263 0.0058 0.0520 1.0000 16.250 1.1514 0.08378 0.07597 0.0052 0.0511 1.0000 16.500 1.1508 0.08719 0.07952 0.0045 0.0502 1.0000 16.750 1.1495 0.09074 0.08318 0.0035 0.0492 1.0000 17.000 1.1482 0.09432 0.08686 0.0025 0.0484 1.0000 17.250 1.1480 0.09774 0.09033 0.0014 0.0476 1.0000 17.500 1.1503 0.10072 0.09333 0.0006 0.0467 1.0000 17.750 1.1402 0.10609 0.09894 -0.0017 0.0462 1.0000 18.000 1.1274 0.11212 0.10520 -0.0045 0.0456 1.0000 18.250 1.1122 0.11879 0.11210 -0.0080 0.0451 1.0000 18.500 1.0925 0.12662 0.12017 -0.0123 0.0448 1.0000 18.750 1.0617 0.13724 0.13104 -0.0186 0.0447 1.0000 |
Polar data table (+)
Polar graphs
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