XFOIL Version 6.96 Calculated polar for: FX 78-K-140 A/20 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.250 -0.1376 0.10985 0.10401 -0.0997 0.7968 0.0418 -11.000 -0.0730 0.09019 0.08485 -0.0951 0.7887 0.0274 -10.750 -0.1317 0.10121 0.09536 -0.1030 0.7945 0.0270 -10.500 -0.1300 0.09729 0.09148 -0.1041 0.7934 0.0265 -10.250 -0.1264 0.09415 0.08835 -0.1051 0.7922 0.0256 -10.000 -0.1263 0.09053 0.08477 -0.1065 0.7910 0.0254 -9.750 -0.1242 0.08755 0.08182 -0.1075 0.7895 0.0245 -9.500 -0.1291 0.08328 0.07765 -0.1092 0.7878 0.0248 -9.250 -0.1313 0.07974 0.07416 -0.1106 0.7861 0.0238 -9.000 -0.1368 0.07571 0.07021 -0.1127 0.7846 0.0238 -8.750 -0.1435 0.07168 0.06624 -0.1152 0.7829 0.0233 -8.500 -0.1572 0.06720 0.06178 -0.1171 0.7810 0.0229 -8.250 -0.1743 0.06375 0.05829 -0.1165 0.7791 0.0226 -8.000 -0.1880 0.06049 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0.07607 0.06803 -0.0054 0.0123 1.0000 14.500 1.1011 0.07943 0.07171 -0.0048 0.0121 1.0000 14.750 1.1021 0.08283 0.07536 -0.0045 0.0122 1.0000 15.000 1.0942 0.08702 0.07988 -0.0044 0.0113 1.0000 15.250 1.0900 0.09130 0.08439 -0.0045 0.0120 1.0000 15.500 1.0793 0.09590 0.08929 -0.0052 0.0115 1.0000 15.750 1.0669 0.10104 0.09469 -0.0063 0.0110 1.0000 16.000 1.0549 0.10644 0.10035 -0.0077 0.0112 1.0000 16.250 1.0416 0.11237 0.10648 -0.0096 0.0117 1.0000 16.500 1.0271 0.11852 0.11287 -0.0124 0.0112 1.0000 16.750 1.0104 0.12559 0.12016 -0.0157 0.0111 1.0000 17.000 0.9973 0.13234 0.12706 -0.0191 0.0119 1.0000 17.250 0.9827 0.13980 0.13465 -0.0230 0.0125 1.0000 17.500 0.9650 0.14878 0.14381 -0.0287 0.0122 1.0000 17.750 0.9481 0.15848 0.15365 -0.0348 0.0123 1.0000 18.000 0.9334 0.16865 0.16390 -0.0411 0.0124 1.0000 18.250 0.9317 0.17403 0.16926 -0.0439 0.0131 1.0000 18.500 0.9184 0.18638 0.18165 -0.0511 0.0129 1.0000 18.750 0.6626 0.16935 0.16533 -0.0390 0.0158 1.0000