XFOIL Version 6.94 Calculated polar for: FX 63-158 AIRFOIL 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 ------- -------- --------- --------- -------- ------- ------- 0.500 0.6696 0.01048 0.00354 -0.1323 0.4500 0.6688 1.000 0.7230 0.01075 0.00376 -0.1317 0.4319 0.6757 1.500 0.7764 0.01108 0.00398 -0.1314 0.4141 0.6825 2.000 0.8313 0.01142 0.00421 -0.1314 0.4000 0.6892 2.500 0.8818 0.01176 0.00452 -0.1305 0.3696 0.6960 3.000 0.9302 0.01233 0.00498 -0.1292 0.3435 0.7040 3.500 0.9839 0.01267 0.00528 -0.1291 0.3263 0.7092 4.000 1.0320 0.01332 0.00573 -0.1282 0.2882 0.7123 4.500 1.0801 0.01375 0.00619 -0.1271 0.2752 0.7169 5.000 1.1241 0.01447 0.00684 -0.1252 0.2368 0.7225 5.500 1.1572 0.01588 0.00791 -0.1218 0.1755 0.7286 6.000 1.1963 0.01681 0.00874 -0.1194 0.1378 0.7331 6.500 1.2270 0.01766 0.00956 -0.1153 0.1031 0.7377 7.000 1.2515 0.01886 0.01068 -0.1104 0.0900 0.7419 7.500 1.2805 0.01991 0.01180 -0.1064 0.0844 0.7463 8.000 1.3070 0.02115 0.01302 -0.1024 0.0599 0.7506 8.500 1.3255 0.02285 0.01475 -0.0977 0.0550 0.7539 9.000 1.3485 0.02434 0.01641 -0.0940 0.0520 0.7582 9.500 1.3639 0.02642 0.01865 -0.0898 0.0461 0.7622 10.000 1.3808 0.02873 0.02097 -0.0866 0.0292 0.7656 10.500 1.3900 0.03197 0.02430 -0.0836 0.0234 0.7685 11.000 1.3922 0.03627 0.02866 -0.0811 0.0119 0.7716 11.500 1.3889 0.04164 0.03410 -0.0792 0.0025 0.7746 12.000 1.3955 0.04646 0.03909 -0.0784 0.0018 0.7771 12.500 1.4025 0.05146 0.04430 -0.0780 0.0016 0.7803 13.000 1.4083 0.05684 0.04989 -0.0779 0.0016 0.7834 13.500 1.4131 0.06270 0.05597 -0.0783 0.0015 0.7866 14.000 1.4174 0.06892 0.06241 -0.0791 0.0015 0.7901 14.500 1.4213 0.07555 0.06927 -0.0803 0.0014 0.7935 15.000 1.4240 0.08266 0.07660 -0.0821 0.0014 0.7969 15.500 1.4265 0.09001 0.08420 -0.0841 0.0014 0.8012 16.000 1.4270 0.09792 0.09237 -0.0866 0.0014 0.8053 16.500 1.4260 0.10632 0.10103 -0.0896 0.0014 0.8095 17.000 1.4237 0.11514 0.11011 -0.0931 0.0014 0.8139 17.500 1.4196 0.12446 0.11968 -0.0973 0.0014 0.8183 18.000 1.4143 0.13406 0.12955 -0.1020 0.0014 0.8238 18.500 1.4074 0.14396 0.13971 -0.1072 0.0014 0.8302 19.000 1.3987 0.15432 0.15033 -0.1131 0.0014 0.8377 19.500 1.3898 0.16471 0.16098 -0.1193 0.0014 0.8475 20.500 1.3685 0.18490 0.18173 -0.1315 0.0015 0.9036