XFOIL Version 6.94 Calculated polar for: NACA 2.5411 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.2913 0.00631 0.00215 -0.0633 0.7539 0.9445 0.500 0.3716 0.00649 0.00215 -0.0681 0.7195 0.9878 1.000 0.4466 0.00669 0.00212 -0.0722 0.6834 1.0000 1.500 0.4960 0.00691 0.00214 -0.0708 0.6488 1.0000 2.000 0.5457 0.00716 0.00222 -0.0694 0.6154 1.0000 2.500 0.5954 0.00744 0.00235 -0.0680 0.5842 1.0000 3.000 0.6457 0.00774 0.00253 -0.0667 0.5547 1.0000 3.500 0.6964 0.00807 0.00273 -0.0656 0.5253 1.0000 4.000 0.7474 0.00841 0.00298 -0.0645 0.4945 1.0000 4.500 0.7985 0.00878 0.00326 -0.0634 0.4618 1.0000 5.000 0.8492 0.00920 0.00359 -0.0624 0.4269 1.0000 5.500 0.8995 0.00967 0.00396 -0.0613 0.3849 1.0000 6.000 0.9477 0.01033 0.00443 -0.0600 0.3290 1.0000 6.500 0.9930 0.01130 0.00508 -0.0583 0.2586 1.0000 7.000 1.0350 0.01260 0.00598 -0.0562 0.1783 1.0000 8.000 1.1153 0.01546 0.00826 -0.0516 0.0742 1.0000 8.500 1.1549 0.01681 0.00953 -0.0491 0.0561 1.0000 9.000 1.1926 0.01818 0.01090 -0.0464 0.0460 1.0000 9.500 1.2256 0.01975 0.01251 -0.0431 0.0394 1.0000 10.000 1.2563 0.02119 0.01404 -0.0394 0.0347 1.0000 11.000 1.2966 0.02529 0.01836 -0.0301 0.0290 1.0000 11.500 1.3199 0.02733 0.02059 -0.0267 0.0267 1.0000 12.000 1.3316 0.03042 0.02376 -0.0228 0.0248 1.0000 12.500 1.3473 0.03346 0.02704 -0.0199 0.0234 1.0000 13.000 1.3604 0.03694 0.03071 -0.0175 0.0222 1.0000 13.500 1.3691 0.04103 0.03493 -0.0156 0.0211 1.0000 14.000 1.3705 0.04617 0.04027 -0.0136 0.0202 1.0000 14.500 1.3744 0.05133 0.04574 -0.0128 0.0195 1.0000 15.000 1.3742 0.05718 0.05186 -0.0128 0.0187 1.0000 15.500 1.3712 0.06373 0.05864 -0.0138 0.0180 1.0000 16.000 1.3657 0.07089 0.06600 -0.0153 0.0174 1.0000 16.500 1.3547 0.07897 0.07427 -0.0169 0.0169 1.0000 17.000 1.3310 0.08948 0.08510 -0.0200 0.0166 1.0000 17.500 1.3062 0.10124 0.09722 -0.0253 0.0164 1.0000 18.000 1.2757 0.11484 0.11119 -0.0324 0.0163 1.0000 18.500 1.2392 0.13054 0.12725 -0.0412 0.0162 1.0000 19.000 1.1944 0.14961 0.14667 -0.0530 0.0163 1.0000