XFOIL Version 6.94 Calculated polar for: E209 (13.72%) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.2356 0.00981 0.00319 -0.0499 0.6317 0.6721 0.500 0.2896 0.00981 0.00325 -0.0494 0.6176 0.7010 1.000 0.3433 0.00984 0.00334 -0.0489 0.6045 0.7367 1.500 0.3957 0.00981 0.00346 -0.0479 0.5911 0.7823 2.000 0.4462 0.00978 0.00368 -0.0464 0.5784 0.8453 2.500 0.5039 0.00988 0.00393 -0.0461 0.5658 0.9174 3.000 0.5833 0.01014 0.00419 -0.0508 0.5526 0.9666 3.500 0.6711 0.01037 0.00438 -0.0577 0.5375 0.9912 4.000 0.7355 0.01052 0.00452 -0.0599 0.5216 1.0000 4.500 0.7787 0.01072 0.00475 -0.0576 0.5065 1.0000 5.000 0.8236 0.01094 0.00499 -0.0555 0.4903 1.0000 5.500 0.8690 0.01118 0.00527 -0.0534 0.4730 1.0000 6.000 0.9148 0.01145 0.00556 -0.0514 0.4538 1.0000 6.500 0.9603 0.01170 0.00591 -0.0494 0.4307 1.0000 7.000 1.0051 0.01204 0.00630 -0.0473 0.4043 1.0000 7.500 1.0476 0.01250 0.00676 -0.0449 0.3687 1.0000 8.000 1.0853 0.01323 0.00741 -0.0418 0.3133 1.0000 8.500 1.1118 0.01464 0.00846 -0.0373 0.2344 1.0000 9.000 1.1320 0.01643 0.00993 -0.0320 0.1673 1.0000 9.500 1.1461 0.01821 0.01150 -0.0258 0.1214 1.0000 10.000 1.1560 0.02015 0.01334 -0.0194 0.0891 1.0000 10.500 1.1614 0.02257 0.01567 -0.0135 0.0657 1.0000 11.000 1.1678 0.02531 0.01847 -0.0089 0.0508 1.0000 11.500 1.1685 0.02894 0.02216 -0.0051 0.0407 1.0000 12.000 1.1729 0.03284 0.02617 -0.0028 0.0340 1.0000 12.500 1.1743 0.03740 0.03091 -0.0012 0.0287 1.0000 13.000 1.1687 0.04299 0.03660 -0.0003 0.0241 1.0000 13.500 1.1696 0.04824 0.04207 0.0003 0.0211 1.0000 14.000 1.1691 0.05388 0.04786 0.0001 0.0190 1.0000 14.500 1.1599 0.06062 0.05472 0.0004 0.0172 1.0000 15.000 1.1629 0.06650 0.06087 -0.0003 0.0161 1.0000 15.500 1.1636 0.07297 0.06759 -0.0014 0.0152 1.0000 16.000 1.1608 0.08026 0.07509 -0.0034 0.0141 1.0000 16.500 1.1572 0.08794 0.08296 -0.0060 0.0135 1.0000 17.000 1.1423 0.09758 0.09286 -0.0091 0.0126 1.0000 17.500 1.1250 0.10869 0.10433 -0.0145 0.0124 1.0000 18.000 1.1036 0.12126 0.11726 -0.0213 0.0121 1.0000 18.500 1.0767 0.13566 0.13201 -0.0295 0.0121 1.0000 19.000 1.0435 0.15254 0.14922 -0.0397 0.0123 1.0000 19.500 1.0012 0.17343 0.17038 -0.0526 0.0125 1.0000 21.000 0.7041 0.23196 0.22969 -0.0852 0.0250 1.0000 21.500 0.7195 0.24054 0.23829 -0.0870 0.0236 1.0000 22.000 0.7256 0.24907 0.24683 -0.0913 0.0234 1.0000 22.500 0.7250 0.25881 0.25657 -0.0974 0.0211 1.0000 23.000 0.7341 0.26669 0.26448 -0.1010 0.0196 1.0000 23.500 0.7444 0.27408 0.27190 -0.1042 0.0184 1.0000 24.000 0.7597 0.28088 0.27874 -0.1060 0.0175 1.0000 24.500 0.7645 0.29113 0.28898 -0.1102 0.0172 1.0000 25.000 0.7674 0.30076 0.29862 -0.1154 0.0155 1.0000 25.500 0.7758 0.30917 0.30706 -0.1190 0.0143 1.0000 26.000 0.7839 0.31730 0.31521 -0.1224 0.0137 1.0000 26.500 0.7958 0.32450 0.32246 -0.1246 0.0127 1.0000 27.500 0.8058 0.34408 0.34206 -0.1327 0.0122 1.0000 28.000 0.8124 0.35342 0.35143 -0.1364 0.0114 1.0000 28.500 0.8193 0.36237 0.36040 -0.1399 0.0108 1.0000 29.000 0.8257 0.37105 0.36910 -0.1432 0.0100 1.0000 29.500 0.8321 0.37935 0.37744 -0.1465 0.0095 1.0000 30.000 0.8381 0.38766 0.38578 -0.1497 0.0092 1.0000 31.000 0.8495 0.40617 0.40433 -0.1558 0.0089 1.0000 31.500 0.8526 0.41627 0.41446 -0.1599 0.0086 1.0000 32.000 0.8574 0.42569 0.42390 -0.1632 0.0081 1.0000 32.500 0.8617 0.43476 0.43300 -0.1665 0.0076 1.0000 33.000 0.8656 0.44384 0.44211 -0.1697 0.0069 1.0000 33.500 0.8690 0.45236 0.45066 -0.1728 0.0067 1.0000 34.000 0.8723 0.46070 0.45903 -0.1760 0.0064 1.0000 34.500 0.8757 0.46915 0.46751 -0.1787 0.0062 1.0000 35.500 0.8796 0.48794 0.48635 -0.1852 0.0061 1.0000 36.000 0.8813 0.49730 0.49573 -0.1884 0.0060 1.0000 36.500 0.8829 0.50619 0.50465 -0.1915 0.0059 1.0000 37.000 0.8844 0.51522 0.51371 -0.1945 0.0057 1.0000 37.500 0.8853 0.52375 0.52226 -0.1974 0.0054 1.0000