XFOIL Version 6.96 Calculated polar for: EPPLER 361 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.250 -0.6810 0.05825 0.05564 -0.0403 1.0000 0.0058 -11.000 -0.7209 0.05004 0.04718 -0.0440 1.0000 0.0058 -10.750 -0.7428 0.04583 0.04280 -0.0435 1.0000 0.0057 -10.500 -0.7613 0.04250 0.03929 -0.0412 1.0000 0.0057 -10.250 -0.7872 0.03874 0.03524 -0.0366 1.0000 0.0057 -10.000 -0.7968 0.03617 0.03244 -0.0327 1.0000 0.0057 -9.750 -0.8030 0.03312 0.02908 -0.0291 1.0000 0.0056 -9.500 -0.8032 0.03043 0.02608 -0.0259 1.0000 0.0056 -9.250 -0.7983 0.02815 0.02349 -0.0230 1.0000 0.0056 -9.000 -0.7904 0.02610 0.02116 -0.0202 1.0000 0.0056 -8.750 -0.7787 0.02447 0.01929 -0.0179 0.9997 0.0056 -8.250 -0.7203 0.02099 0.01529 -0.0202 0.9580 0.0057 -8.000 -0.6826 0.01960 0.01368 -0.0229 0.9265 0.0057 -7.750 -0.6554 0.01855 0.01237 -0.0230 0.8906 0.0058 -7.500 -0.6356 0.01761 0.01121 -0.0216 0.8605 0.0059 -7.250 -0.6155 0.01684 0.01026 -0.0202 0.8360 0.0059 -6.750 -0.5734 0.01554 0.00868 -0.0178 0.7997 0.0062 -6.250 -0.5282 0.01456 0.00749 -0.0158 0.7690 0.0065 -6.000 -0.5051 0.01410 0.00693 -0.0149 0.7556 0.0069 -5.750 -0.4816 0.01368 0.00641 -0.0141 0.7438 0.0071 -5.500 -0.4579 0.01330 0.00593 -0.0133 0.7328 0.0074 -5.250 -0.4337 0.01295 0.00550 -0.0126 0.7217 0.0078 -5.000 -0.4097 0.01256 0.00504 -0.0118 0.7115 0.0083 -4.750 -0.3852 0.01226 0.00467 -0.0111 0.7020 0.0091 -4.500 -0.3600 0.01198 0.00433 -0.0105 0.6930 0.0101 -4.250 -0.3352 0.01170 0.00400 -0.0099 0.6847 0.0117 -4.000 -0.3100 0.01144 0.00372 -0.0094 0.6761 0.0147 -3.750 -0.2848 0.01120 0.00345 -0.0088 0.6684 0.0199 -3.500 -0.2596 0.01093 0.00322 -0.0083 0.6609 0.0304 -3.000 -0.2092 0.01042 0.00282 -0.0073 0.6469 0.0658 -2.750 -0.1848 0.01011 0.00262 -0.0067 0.6401 0.1028 -2.500 -0.1616 0.00965 0.00242 -0.0059 0.6341 0.1720 -2.250 -0.1395 0.00911 0.00222 -0.0050 0.6277 0.2691 -2.000 -0.1194 0.00846 0.00201 -0.0038 0.6219 0.3969 -1.750 -0.1003 0.00780 0.00184 -0.0022 0.6165 0.5303 -1.500 -0.0795 0.00738 0.00177 -0.0007 0.6107 0.6313 -1.000 -0.0304 0.00711 0.00176 0.0010 0.6002 0.7290 -0.750 -0.0052 0.00706 0.00179 0.0018 0.5947 0.7681 -0.500 0.0207 0.00706 0.00181 0.0024 0.5896 0.7942 -0.250 0.0475 0.00706 0.00183 0.0029 0.5846 0.8126 0.000 0.0745 0.00708 0.00185 0.0033 0.5791 0.8264 0.250 0.1017 0.00711 0.00187 0.0036 0.5740 0.8370 0.500 0.1291 0.00713 0.00187 0.0038 0.5684 0.8462 0.750 0.1568 0.00715 0.00188 0.0039 0.5610 0.8524 1.000 0.1843 0.00719 0.00188 0.0041 0.5521 0.8586 1.500 0.2391 0.00727 0.00188 0.0044 0.5284 0.8696 1.750 0.2663 0.00732 0.00189 0.0046 0.5152 0.8756 2.000 0.2937 0.00738 0.00192 0.0048 0.5039 0.8810 2.250 0.3212 0.00744 0.00196 0.0049 0.4938 0.8866 2.500 0.3485 0.00749 0.00200 0.0051 0.4832 0.8928 2.750 0.3760 0.00757 0.00206 0.0052 0.4701 0.8981 3.000 0.4033 0.00766 0.00212 0.0053 0.4542 0.9040 3.250 0.4298 0.00777 0.00218 0.0056 0.4374 0.9107 3.500 0.4571 0.00794 0.00228 0.0057 0.4131 0.9160 3.750 0.4832 0.00817 0.00240 0.0059 0.3818 0.9225 4.000 0.5090 0.00846 0.00256 0.0062 0.3464 0.9289 4.250 0.5356 0.00884 0.00278 0.0062 0.3066 0.9348 4.500 0.5603 0.00926 0.00302 0.0065 0.2664 0.9421 4.750 0.5888 0.00968 0.00330 0.0061 0.2323 0.9470 5.000 0.6173 0.01003 0.00355 0.0056 0.2071 0.9525 5.250 0.6445 0.01038 0.00380 0.0054 0.1852 0.9586 5.500 0.6754 0.01073 0.00408 0.0044 0.1659 0.9624 5.750 0.7047 0.01105 0.00434 0.0038 0.1523 0.9674 6.000 0.7331 0.01136 0.00462 0.0034 0.1414 0.9726 6.250 0.7647 0.01171 0.00491 0.0022 0.1302 0.9756 6.500 0.7957 0.01198 0.00519 0.0012 0.1228 0.9792 6.750 0.8238 0.01232 0.00550 0.0007 0.1159 0.9840 7.000 0.8563 0.01261 0.00580 -0.0006 0.1096 0.9863 7.250 0.8872 0.01298 0.00614 -0.0018 0.1034 0.9895 7.500 0.9176 0.01327 0.00647 -0.0027 0.0990 0.9929 7.750 0.9483 0.01362 0.00681 -0.0038 0.0940 0.9959 8.000 0.9794 0.01400 0.00721 -0.0050 0.0895 0.9988 8.250 1.0040 0.01430 0.00754 -0.0048 0.0861 1.0000 8.500 1.0203 0.01461 0.00786 -0.0029 0.0827 1.0000 8.750 1.0361 0.01498 0.00823 -0.0009 0.0793 1.0000 9.000 1.0531 0.01530 0.00859 0.0008 0.0768 1.0000 9.250 1.0703 0.01563 0.00896 0.0026 0.0738 1.0000 9.500 1.0866 0.01601 0.00935 0.0043 0.0708 1.0000 9.750 1.1015 0.01647 0.00980 0.0063 0.0675 1.0000 10.000 1.1182 0.01682 0.01021 0.0080 0.0653 1.0000 10.250 1.1339 0.01723 0.01066 0.0098 0.0628 1.0000 10.500 1.1484 0.01769 0.01114 0.0118 0.0601 1.0000 10.750 1.1595 0.01822 0.01168 0.0142 0.0575 1.0000 11.000 1.1716 0.01865 0.01218 0.0166 0.0557 1.0000 11.250 1.1832 0.01916 0.01275 0.0188 0.0535 1.0000 11.500 1.1941 0.01978 0.01339 0.0209 0.0512 1.0000 11.750 1.2036 0.02053 0.01416 0.0230 0.0489 1.0000 12.000 1.2159 0.02120 0.01490 0.0246 0.0471 1.0000 12.250 1.2271 0.02198 0.01574 0.0261 0.0451 1.0000 12.500 1.2371 0.02290 0.01670 0.0275 0.0430 1.0000 12.750 1.2455 0.02400 0.01783 0.0289 0.0410 1.0000 13.000 1.2562 0.02500 0.01892 0.0299 0.0397 1.0000 13.250 1.2660 0.02612 0.02012 0.0309 0.0380 1.0000 13.500 1.2745 0.02740 0.02144 0.0318 0.0364 1.0000 13.750 1.2814 0.02887 0.02295 0.0326 0.0348 1.0000 14.000 1.2891 0.03032 0.02450 0.0332 0.0337 1.0000 14.250 1.2967 0.03183 0.02609 0.0337 0.0324 1.0000 14.500 1.3032 0.03348 0.02781 0.0342 0.0310 1.0000 14.750 1.3079 0.03535 0.02974 0.0345 0.0298 1.0000 15.000 1.3100 0.03751 0.03197 0.0347 0.0287 1.0000 15.250 1.3154 0.03941 0.03398 0.0349 0.0277 1.0000 15.500 1.3190 0.04151 0.03617 0.0349 0.0265 1.0000 15.750 1.3205 0.04390 0.03865 0.0348 0.0259 1.0000 16.000 1.3208 0.04646 0.04129 0.0345 0.0249 1.0000 16.250 1.3182 0.04941 0.04431 0.0341 0.0239 1.0000 16.500 1.3170 0.05233 0.04733 0.0335 0.0234 1.0000 16.750 1.3160 0.05531 0.05043 0.0328 0.0226 1.0000 17.000 1.3132 0.05863 0.05386 0.0319 0.0220 1.0000 17.250 1.3090 0.06225 0.05758 0.0308 0.0213 1.0000 17.500 1.3030 0.06621 0.06164 0.0293 0.0207 1.0000 17.750 1.2945 0.07066 0.06619 0.0276 0.0202 1.0000 18.000 1.2840 0.07559 0.07123 0.0255 0.0198 1.0000 18.250 1.2717 0.08096 0.07671 0.0232 0.0194 1.0000 18.500 1.2598 0.08640 0.08228 0.0207 0.0192 1.0000 18.750 1.2486 0.09191 0.08792 0.0180 0.0187 1.0000 19.000 1.2339 0.09815 0.09430 0.0149 0.0184 1.0000 19.250 1.2172 0.10488 0.10117 0.0115 0.0182 1.0000