XFOIL Version 6.94 Calculated polar for: MA409 (smoothed) 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 0.4250 0.00713 0.00204 -0.1028 0.8352 0.4665 0.500 0.4779 0.00672 0.00203 -0.1017 0.8010 0.6261 1.000 0.5298 0.00605 0.00205 -0.0995 0.7605 1.0000 1.500 0.5826 0.00632 0.00207 -0.0982 0.7135 1.0000 2.000 0.6347 0.00667 0.00216 -0.0969 0.6630 1.0000 2.500 0.6859 0.00710 0.00232 -0.0954 0.6065 1.0000 3.000 0.7369 0.00759 0.00255 -0.0941 0.5509 1.0000 3.500 0.7875 0.00813 0.00283 -0.0927 0.4938 1.0000 4.000 0.8375 0.00876 0.00318 -0.0913 0.4338 1.0000 4.500 0.8876 0.00942 0.00358 -0.0900 0.3746 1.0000 5.000 0.9375 0.01011 0.00403 -0.0887 0.3174 1.0000 5.500 0.9865 0.01092 0.00457 -0.0873 0.2595 1.0000 6.000 1.0344 0.01186 0.00523 -0.0859 0.2004 1.0000 6.500 1.0804 0.01299 0.00604 -0.0842 0.1380 1.0000 7.000 1.1230 0.01451 0.00716 -0.0820 0.0763 1.0000 7.500 1.1659 0.01592 0.00841 -0.0798 0.0537 1.0000 8.000 1.2084 0.01728 0.00975 -0.0775 0.0445 1.0000 8.500 1.2499 0.01861 0.01114 -0.0750 0.0389 1.0000 9.000 1.2874 0.02018 0.01274 -0.0721 0.0351 1.0000 9.500 1.3254 0.02156 0.01423 -0.0692 0.0321 1.0000 10.000 1.3566 0.02337 0.01616 -0.0654 0.0298 1.0000 10.500 1.3831 0.02516 0.01802 -0.0610 0.0279 1.0000 11.000 1.4037 0.02751 0.02052 -0.0561 0.0266 1.0000 11.500 1.4253 0.02976 0.02296 -0.0517 0.0253 1.0000 12.000 1.4440 0.03228 0.02557 -0.0477 0.0242 1.0000 12.500 1.4577 0.03554 0.02903 -0.0436 0.0231 1.0000 13.000 1.4699 0.03896 0.03272 -0.0400 0.0222 1.0000 13.500 1.4785 0.04287 0.03685 -0.0370 0.0214 1.0000 14.000 1.4844 0.04739 0.04163 -0.0345 0.0211 1.0000 14.500 1.4889 0.05221 0.04655 -0.0327 0.0205 1.0000 15.000 1.4769 0.05936 0.05408 -0.0318 0.0200 1.0000 15.500 1.4610 0.06745 0.06254 -0.0323 0.0199 1.0000 16.000 1.4346 0.07772 0.07326 -0.0358 0.0195 1.0000 16.500 1.3998 0.09070 0.08666 -0.0416 0.0190 1.0000 17.000 1.3630 0.10517 0.10151 -0.0492 0.0188 1.0000 17.500 1.3126 0.12378 0.12054 -0.0600 0.0191 1.0000 18.000 1.2329 0.15191 0.14916 -0.0783 0.0195 1.0000