XFOIL Version 6.94 Calculated polar for: E392 (10.15%) 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 0.4394 0.00703 0.00222 -0.0943 0.6572 0.9098 0.500 0.5047 0.00705 0.00213 -0.0962 0.6459 1.0000 1.000 0.5614 0.00723 0.00217 -0.0964 0.6345 1.0000 1.500 0.6180 0.00740 0.00227 -0.0966 0.6231 1.0000 2.000 0.6743 0.00761 0.00241 -0.0968 0.6120 1.0000 2.500 0.7303 0.00783 0.00253 -0.0968 0.5998 1.0000 3.000 0.7859 0.00798 0.00270 -0.0968 0.5855 1.0000 3.500 0.8412 0.00817 0.00288 -0.0967 0.5709 1.0000 4.000 0.8961 0.00836 0.00311 -0.0966 0.5549 1.0000 4.500 0.9506 0.00858 0.00334 -0.0963 0.5373 1.0000 5.000 1.0042 0.00884 0.00362 -0.0960 0.5171 1.0000 5.500 1.0559 0.00910 0.00387 -0.0952 0.4785 1.0000 6.000 1.1058 0.00960 0.00429 -0.0942 0.4298 1.0000 6.500 1.1505 0.01055 0.00494 -0.0926 0.3479 1.0000 7.000 1.1846 0.01252 0.00624 -0.0897 0.2196 1.0000 7.500 1.2159 0.01466 0.00779 -0.0865 0.1150 1.0000 8.000 1.2397 0.01720 0.00977 -0.0821 0.0300 1.0000 8.500 1.2709 0.01890 0.01151 -0.0785 0.0201 1.0000 9.000 1.2929 0.02074 0.01356 -0.0734 0.0180 1.0000 9.500 1.3094 0.02272 0.01576 -0.0680 0.0169 1.0000 10.000 1.3230 0.02511 0.01832 -0.0631 0.0157 1.0000 10.500 1.3325 0.02815 0.02155 -0.0588 0.0148 1.0000 11.000 1.3389 0.03192 0.02551 -0.0552 0.0143 1.0000 11.500 1.3435 0.03640 0.03020 -0.0521 0.0137 1.0000 12.000 1.3518 0.04124 0.03530 -0.0493 0.0133 1.0000 12.500 1.3643 0.04648 0.04086 -0.0468 0.0128 1.0000 13.000 1.3733 0.05121 0.04591 -0.0456 0.0123 1.0000 13.500 1.3759 0.05732 0.05239 -0.0447 0.0119 1.0000 14.000 1.3694 0.06484 0.06031 -0.0446 0.0116 1.0000 14.500 1.3527 0.07411 0.07001 -0.0459 0.0115 1.0000 15.000 1.3278 0.08523 0.08156 -0.0491 0.0114 1.0000 15.500 1.2963 0.09855 0.09530 -0.0546 0.0114 1.0000 16.000 1.2601 0.11418 0.11132 -0.0627 0.0115 1.0000 16.500 1.2197 0.13269 0.13019 -0.0739 0.0117 1.0000 17.000 1.1757 0.15475 0.15257 -0.0882 0.0121 1.0000