XFOIL Version 6.96 Calculated polar for: GOE 233 (MVA CA4) AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.000 -0.2379 0.13882 0.13514 -0.0443 1.0000 0.0458 -11.750 -0.2576 0.13864 0.13506 -0.0446 1.0000 0.0470 -11.500 -0.2759 0.13830 0.13481 -0.0428 1.0000 0.0472 -11.250 -0.2633 0.13483 0.13135 -0.0390 1.0000 0.0478 -11.000 -0.2668 0.13391 0.13048 -0.0357 1.0000 0.0485 -10.750 -0.2496 0.13064 0.12720 -0.0384 0.9979 0.0501 -10.500 -0.2348 0.12683 0.12338 -0.0441 0.9951 0.0540 -10.250 -0.2258 0.12232 0.11888 -0.0505 0.9917 0.0554 -10.000 -0.2008 0.11865 0.11519 -0.0515 0.9892 0.0569 -9.750 -0.1807 0.11521 0.11173 -0.0550 0.9862 0.0592 -9.500 -0.1745 0.11218 0.10869 -0.0660 0.9816 0.0635 -9.250 -0.1594 0.10717 0.10369 -0.0688 0.9771 0.0644 -9.000 -0.1309 0.10344 0.09994 -0.0691 0.9751 0.0659 -8.750 -0.1068 0.10020 0.09668 -0.0725 0.9724 0.0689 -8.500 -0.1024 0.09756 0.09405 -0.0858 0.9628 0.0741 -8.250 -0.0802 0.09215 0.08863 -0.0868 0.9605 0.0753 -8.000 -0.0516 0.08874 0.08519 -0.0877 0.9583 0.0768 -7.750 -0.0268 0.08557 0.08199 -0.0910 0.9550 0.0793 -7.500 -0.0145 0.08293 0.07935 -0.0934 0.9454 0.0824 -7.250 -0.0167 0.07894 0.07539 -0.1061 0.9292 0.0865 -7.000 0.0024 0.07609 0.07252 -0.1026 0.9255 0.0878 -6.750 0.0768 0.02930 0.02438 -0.1909 0.9091 0.0556 -6.500 0.1300 0.02553 0.01997 -0.2006 0.9060 0.0549 -6.250 0.1637 0.02313 0.01733 -0.2038 0.8983 0.0558 -6.000 0.1983 0.02156 0.01558 -0.2060 0.8929 0.0567 -5.750 0.2335 0.02015 0.01397 -0.2078 0.8888 0.0571 -5.500 0.2628 0.01925 0.01295 -0.2084 0.8801 0.0578 -5.250 0.2945 0.01838 0.01198 -0.2090 0.8745 0.0587 -5.000 0.3246 0.01774 0.01128 -0.2094 0.8675 0.0600 -4.750 0.3549 0.01721 0.01065 -0.2097 0.8604 0.0621 -4.500 0.3862 0.01666 0.01002 -0.2101 0.8552 0.0643 -4.250 0.4159 0.01623 0.00962 -0.2105 0.8463 0.0671 -4.000 0.4475 0.01578 0.00908 -0.2110 0.8403 0.0711 -3.750 0.4788 0.01534 0.00861 -0.2118 0.8317 0.0778 -3.500 0.5137 0.01446 0.00776 -0.2136 0.8249 0.1077 -3.250 0.5463 0.01381 0.00725 -0.2150 0.8175 0.1883 -3.000 0.5751 0.01380 0.00733 -0.2149 0.8100 0.2306 -2.750 0.6035 0.01395 0.00743 -0.2145 0.8040 0.2542 -2.500 0.6307 0.01422 0.00767 -0.2140 0.7958 0.2702 -2.250 0.6584 0.01453 0.00790 -0.2134 0.7899 0.2845 -2.000 0.6859 0.01485 0.00814 -0.2130 0.7824 0.2972 -1.750 0.7115 0.01538 0.00873 -0.2118 0.7758 0.3031 -1.500 0.7394 0.01569 0.00895 -0.2113 0.7702 0.3142 -1.250 0.7645 0.01618 0.00952 -0.2102 0.7625 0.3190 -1.000 0.7930 0.01637 0.00958 -0.2099 0.7567 0.3299 -0.750 0.8164 0.01702 0.01038 -0.2083 0.7500 0.3351 -0.500 0.8447 0.01719 0.01047 -0.2082 0.7435 0.3467 -0.250 0.8711 0.01741 0.01069 -0.2073 0.7385 0.3507 0.000 0.9004 0.01745 0.01064 -0.2077 0.7310 0.3618 0.250 0.9259 0.01755 0.01079 -0.2067 0.7243 0.3656 0.500 0.9530 0.01762 0.01084 -0.2063 0.7168 0.3724 0.750 0.9822 0.01750 0.01063 -0.2065 0.7093 0.3795 1.000 1.0095 0.01751 0.01063 -0.2062 0.7029 0.3836 1.250 1.0380 0.01748 0.01056 -0.2063 0.6953 0.3891 1.500 1.0680 0.01736 0.01030 -0.2066 0.6891 0.3947 1.750 1.0935 0.01743 0.01048 -0.2060 0.6805 0.3996 2.000 1.1231 0.01743 0.01035 -0.2062 0.6738 0.4072 2.250 1.1494 0.01744 0.01042 -0.2059 0.6660 0.4119 2.500 1.1769 0.01745 0.01043 -0.2056 0.6587 0.4173 2.750 1.2057 0.01749 0.01040 -0.2058 0.6515 0.4213 3.000 1.2345 0.01748 0.01033 -0.2060 0.6436 0.4238 3.250 1.2621 0.01745 0.01030 -0.2059 0.6363 0.4259 3.500 1.2887 0.01747 0.01037 -0.2056 0.6278 0.4285 3.750 1.3164 0.01752 0.01038 -0.2054 0.6201 0.4319 4.000 1.3429 0.01756 0.01044 -0.2051 0.6105 0.4348 4.250 1.3708 0.01764 0.01046 -0.2050 0.6028 0.4373 4.500 1.3973 0.01771 0.01057 -0.2048 0.5941 0.4396 4.750 1.4244 0.01778 0.01065 -0.2046 0.5869 0.4420 5.000 1.4496 0.01787 0.01085 -0.2040 0.5778 0.4446 5.250 1.4764 0.01799 0.01095 -0.2037 0.5703 0.4482 5.500 1.5012 0.01812 0.01116 -0.2031 0.5607 0.4518 5.750 1.5271 0.01826 0.01130 -0.2027 0.5519 0.4546 6.000 1.5516 0.01832 0.01145 -0.2020 0.5418 0.4572 6.250 1.5755 0.01846 0.01166 -0.2012 0.5310 0.4600 6.500 1.5993 0.01858 0.01182 -0.2003 0.5193 0.4632 6.750 1.6217 0.01873 0.01196 -0.1992 0.5051 0.4667 7.000 1.6428 0.01894 0.01218 -0.1979 0.4887 0.4703 7.250 1.6623 0.01918 0.01246 -0.1963 0.4702 0.4737 7.500 1.6799 0.01954 0.01282 -0.1944 0.4490 0.4773 7.750 1.6961 0.02003 0.01325 -0.1923 0.4271 0.4806 8.000 1.7113 0.02061 0.01379 -0.1901 0.4051 0.4839 8.250 1.7244 0.02126 0.01440 -0.1877 0.3814 0.4868 8.500 1.7346 0.02202 0.01512 -0.1847 0.3571 0.4900 8.750 1.7416 0.02287 0.01592 -0.1813 0.3324 0.4936 9.000 1.7432 0.02389 0.01685 -0.1771 0.3114 0.4972 9.250 1.7477 0.02504 0.01793 -0.1737 0.2920 0.5009 9.500 1.7519 0.02628 0.01914 -0.1704 0.2757 0.5043 9.750 1.7558 0.02765 0.02049 -0.1673 0.2616 0.5079 10.000 1.7589 0.02914 0.02196 -0.1643 0.2485 0.5117 10.250 1.7620 0.03073 0.02353 -0.1614 0.2351 0.5156 10.500 1.7649 0.03238 0.02522 -0.1587 0.2204 0.5193 10.750 1.7651 0.03433 0.02718 -0.1560 0.2034 0.5234 11.000 1.7642 0.03652 0.02937 -0.1534 0.1752 0.5282 11.250 1.7499 0.04004 0.03260 -0.1502 0.1253 0.5315 11.500 1.7310 0.04424 0.03652 -0.1470 0.0955 0.5341 11.750 1.7174 0.04810 0.04032 -0.1444 0.0827 0.5376 12.000 1.7090 0.05160 0.04388 -0.1423 0.0752 0.5425 12.250 1.6984 0.05546 0.04777 -0.1404 0.0703 0.5473 12.500 1.6933 0.05887 0.05131 -0.1390 0.0662 0.5533 12.750 1.6883 0.06237 0.05491 -0.1377 0.0627 0.5607 13.000 1.6789 0.06646 0.05906 -0.1365 0.0600 0.5681 13.250 1.6735 0.07014 0.06287 -0.1355 0.0575 0.5802 13.500 1.6722 0.07341 0.06633 -0.1347 0.0550 0.6091 13.750 1.6664 0.07649 0.06974 -0.1335 0.0530 1.0000 14.000 1.6612 0.08021 0.07347 -0.1326 0.0511 1.0000 14.250 1.6570 0.08365 0.07691 -0.1315 0.0492 1.0000 14.500 1.6582 0.08670 0.08008 -0.1309 0.0474 1.0000 14.750 1.6585 0.08981 0.08327 -0.1303 0.0455 1.0000 15.000 1.6590 0.09283 0.08631 -0.1297 0.0439 1.0000