XFOIL Version 6.94 Calculated polar for: S2046 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 0.3857 0.00659 0.00199 -0.0918 0.8213 0.6872 0.500 0.4397 0.00660 0.00203 -0.0907 0.7973 0.7324 1.000 0.4934 0.00661 0.00208 -0.0897 0.7692 0.7683 1.500 0.5468 0.00664 0.00211 -0.0886 0.7374 0.8003 2.000 0.5986 0.00668 0.00216 -0.0872 0.6988 0.8376 2.500 0.6452 0.00665 0.00218 -0.0845 0.6465 0.9082 3.000 0.7005 0.00712 0.00229 -0.0842 0.5531 1.0000 3.500 0.7514 0.00788 0.00261 -0.0833 0.4626 1.0000 4.000 0.8028 0.00862 0.00303 -0.0825 0.3888 1.0000 4.500 0.8544 0.00936 0.00349 -0.0818 0.3278 1.0000 5.000 0.9059 0.01008 0.00401 -0.0811 0.2712 1.0000 5.500 0.9560 0.01097 0.00461 -0.0802 0.2053 1.0000 6.000 1.0029 0.01228 0.00547 -0.0790 0.1228 1.0000 6.500 1.0500 0.01355 0.00654 -0.0777 0.0811 1.0000 7.000 1.0977 0.01470 0.00764 -0.0764 0.0639 1.0000 7.500 1.1436 0.01599 0.00901 -0.0747 0.0545 1.0000 8.000 1.1882 0.01733 0.01040 -0.0730 0.0470 1.0000 9.000 1.2758 0.01993 0.01327 -0.0693 0.0375 1.0000 11.000 1.4130 0.02722 0.02122 -0.0578 0.0229 1.0000 11.500 1.4367 0.02878 0.02293 -0.0536 0.0202 1.0000 12.000 1.4357 0.03288 0.02724 -0.0475 0.0178 1.0000 12.500 1.4520 0.03534 0.02998 -0.0440 0.0164 1.0000 13.000 1.4622 0.03858 0.03345 -0.0410 0.0149 1.0000 13.500 1.4667 0.04269 0.03777 -0.0390 0.0138 1.0000 14.000 1.4483 0.05026 0.04564 -0.0379 0.0130 1.0000 14.500 1.4223 0.06006 0.05586 -0.0394 0.0126 1.0000 15.000 1.4031 0.07014 0.06632 -0.0431 0.0123 1.0000 15.500 1.3749 0.08316 0.07972 -0.0497 0.0121 1.0000 16.000 1.3383 0.09948 0.09641 -0.0591 0.0121 1.0000 16.500 1.2941 0.11906 0.11635 -0.0712 0.0122 1.0000 17.000 1.2374 0.14350 0.14114 -0.0868 0.0124 1.0000 19.000 0.8625 0.24508 0.24344 -0.1353 0.0187 1.0000 19.500 0.8729 0.25494 0.25331 -0.1378 0.0178 1.0000 20.000 0.8775 0.26508 0.26346 -0.1426 0.0175 1.0000 20.500 0.8820 0.27553 0.27392 -0.1478 0.0159 1.0000 21.000 0.8910 0.28434 0.28274 -0.1512 0.0141 1.0000 21.500 0.9027 0.29134 0.28979 -0.1536 0.0130 1.0000