XFOIL Version 6.94 Calculated polar for: E212 (10.55%) 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 0.4613 0.00832 0.00339 -0.1187 0.8792 0.7064 0.500 0.5282 0.00809 0.00321 -0.1201 0.8550 0.7520 1.000 0.5839 0.00803 0.00321 -0.1192 0.8228 0.7948 1.500 0.6361 0.00807 0.00325 -0.1176 0.7871 0.8382 2.000 0.6806 0.00814 0.00331 -0.1142 0.7477 0.8829 2.500 0.7178 0.00814 0.00329 -0.1093 0.7058 0.9431 3.000 0.7769 0.00839 0.00337 -0.1099 0.6585 1.0000 3.500 0.8304 0.00886 0.00364 -0.1094 0.6077 1.0000 4.000 0.8812 0.00941 0.00398 -0.1083 0.5533 1.0000 4.500 0.9303 0.01003 0.00442 -0.1069 0.4970 1.0000 5.000 0.9774 0.01078 0.00493 -0.1053 0.4368 1.0000 5.500 1.0214 0.01172 0.00557 -0.1031 0.3585 1.0000 6.000 1.0645 0.01283 0.00634 -0.1010 0.2826 1.0000 6.500 1.1067 0.01409 0.00727 -0.0989 0.2053 1.0000 7.000 1.1480 0.01548 0.00835 -0.0967 0.1406 1.0000 7.500 1.1870 0.01708 0.00965 -0.0942 0.0823 1.0000 8.000 1.2150 0.01973 0.01191 -0.0898 0.0263 1.0000 8.500 1.2458 0.02183 0.01415 -0.0857 0.0210 1.0000 9.000 1.2723 0.02379 0.01631 -0.0809 0.0190 1.0000 9.500 1.2926 0.02614 0.01883 -0.0756 0.0177 1.0000 10.000 1.3059 0.02935 0.02220 -0.0699 0.0168 1.0000 10.500 1.3221 0.03341 0.02648 -0.0651 0.0164 1.0000 11.000 1.3432 0.03672 0.03011 -0.0613 0.0158 1.0000 11.500 1.3593 0.04059 0.03435 -0.0576 0.0152 1.0000 12.000 1.3686 0.04562 0.03980 -0.0540 0.0150 1.0000 12.500 1.3665 0.05180 0.04645 -0.0507 0.0149 1.0000 13.000 1.3517 0.05944 0.05460 -0.0485 0.0150 1.0000 13.500 1.3258 0.06891 0.06458 -0.0486 0.0151 1.0000 14.000 1.2919 0.08059 0.07672 -0.0519 0.0152 1.0000 14.500 1.2529 0.09481 0.09138 -0.0587 0.0154 1.0000 15.000 1.2112 0.11183 0.10878 -0.0690 0.0157 1.0000 15.500 1.1670 0.13212 0.12939 -0.0825 0.0160 1.0000 16.000 1.1252 0.15439 0.15189 -0.0971 0.0165 1.0000 18.000 0.8324 0.22470 0.22279 -0.1275 0.0300 1.0000 18.500 0.8469 0.23468 0.23279 -0.1292 0.0286 1.0000 19.000 0.8504 0.24400 0.24212 -0.1342 0.0284 1.0000 19.500 0.8497 0.25392 0.25204 -0.1407 0.0258 1.0000 20.000 0.8587 0.26246 0.26060 -0.1442 0.0240 1.0000 21.000 1.1424 0.29013 0.28764 -0.1755 0.0205 1.0000 21.500 1.1570 0.29756 0.29507 -0.1807 0.0187 1.0000 22.000 1.1724 0.30386 0.30138 -0.1849 0.0175 1.0000 22.500 1.1897 0.30961 0.30716 -0.1877 0.0167 1.0000 23.000 1.2051 0.31835 0.31590 -0.1915 0.0164 1.0000 23.500 1.2155 0.32542 0.32294 -0.1998 0.0155 1.0000 24.000 1.2300 0.33228 0.32981 -0.2048 0.0143 1.0000 24.500 1.2443 0.33821 0.33576 -0.2093 0.0132 1.0000 25.000 1.2587 0.34317 0.34075 -0.2131 0.0126 1.0000 25.500 1.2741 0.35085 0.34844 -0.2161 0.0122 1.0000 26.000 1.2858 0.35602 0.35358 -0.2238 0.0117 1.0000 26.500 1.3000 0.36206 0.35963 -0.2289 0.0106 1.0000 27.000 1.3135 0.36729 0.36488 -0.2337 0.0099 1.0000 27.500 1.3262 0.37209 0.36969 -0.2383 0.0094 1.0000 28.000 1.3384 0.37663 0.37427 -0.2425 0.0090 1.0000 28.500 1.3514 0.38406 0.38172 -0.2454 0.0087 1.0000 29.000 1.3627 0.38788 0.38552 -0.2527 0.0085 1.0000 29.500 1.3756 0.39363 0.39128 -0.2579 0.0078 1.0000 30.000 1.3872 0.39870 0.39635 -0.2628 0.0071 1.0000 30.500 1.3980 0.40340 0.40108 -0.2676 0.0067 1.0000 31.000 1.4083 0.40777 0.40547 -0.2723 0.0063 1.0000 31.500 1.4174 0.41201 0.40975 -0.2764 0.0060 1.0000 32.500 1.4365 0.42243 0.42018 -0.2861 0.0059 1.0000 33.000 1.4468 0.42718 0.42493 -0.2916 0.0058 1.0000 33.500 1.4569 0.43232 0.43009 -0.2967 0.0055 1.0000 34.000 1.4657 0.43704 0.43482 -0.3015 0.0051 1.0000 34.500 1.4737 0.44146 0.43928 -0.3064 0.0047 1.0000 35.000 1.4808 0.44557 0.44341 -0.3111 0.0043 1.0000 35.500 1.4875 0.44952 0.44738 -0.3160 0.0041 1.0000 36.000 1.4931 0.45315 0.45104 -0.3207 0.0039 1.0000 36.500 1.4975 0.45725 0.45517 -0.3247 0.0038 1.0000 37.500 1.5101 0.46588 0.46382 -0.3350 0.0037 1.0000 38.000 1.5167 0.47044 0.46840 -0.3401 0.0036 1.0000 38.500 1.5219 0.47465 0.47263 -0.3449 0.0034 1.0000 39.000 1.5266 0.47874 0.47674 -0.3497 0.0032 1.0000 39.500 1.5302 0.48250 0.48052 -0.3544 0.0030 1.0000 40.000 1.5334 0.48616 0.48421 -0.3592 0.0028 1.0000 40.500 1.5359 0.48965 0.48774 -0.3640 0.0027 1.0000 41.000 1.5379 0.49306 0.49117 -0.3687 0.0025 1.0000 41.500 1.5395 0.49634 0.49447 -0.3735 0.0024 1.0000 42.000 1.5403 0.49942 0.49758 -0.3783 0.0023 1.0000 42.500 1.5407 0.50240 0.50059 -0.3831 0.0022 1.0000 43.000 1.5398 0.50510 0.50333 -0.3877 0.0022 1.0000 43.500 1.5381 0.50811 0.50637 -0.3920 0.0021 1.0000