XFOIL Version 6.96 Calculated polar for: FX 78-K-150/20 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.000 -0.1148 0.10995 0.10551 -0.1131 0.8042 0.0501 -11.750 -0.1229 0.10690 0.10254 -0.1163 0.8028 0.0510 -11.500 -0.1287 0.10364 0.09934 -0.1189 0.8016 0.0513 -11.250 -0.1289 0.10025 0.09599 -0.1207 0.8004 0.0514 -11.000 -0.1210 0.09502 0.09078 -0.1197 0.7996 0.0527 -10.750 -0.1086 0.09279 0.08854 -0.1189 0.7983 0.0541 -10.500 -0.1020 0.09037 0.08613 -0.1190 0.7972 0.0559 -10.250 -0.1010 0.08754 0.08332 -0.1199 0.7960 0.0567 -10.000 -0.1024 0.08441 0.08022 -0.1208 0.7948 0.0578 -9.750 -0.1067 0.08112 0.07696 -0.1220 0.7934 0.0595 -9.500 -0.1368 0.07540 0.07133 -0.1280 0.7918 0.0631 -9.250 -0.1655 0.07129 0.06722 -0.1303 0.7902 0.0635 -9.000 -0.1830 0.06862 0.06457 -0.1291 0.7886 0.0635 -8.750 -0.2134 0.06731 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-0.0625 0.6686 1.0000 2.750 0.4184 0.03813 0.03202 -0.0613 0.6660 1.0000 3.000 0.4480 0.03806 0.03191 -0.0614 0.6645 1.0000 3.250 0.4816 0.03793 0.03176 -0.0620 0.6634 1.0000 3.500 0.4615 0.03919 0.03301 -0.0565 0.6525 1.0000 3.750 0.4917 0.03922 0.03304 -0.0569 0.6509 1.0000 4.000 0.4964 0.04022 0.03404 -0.0548 0.6435 1.0000 4.250 0.5184 0.04055 0.03437 -0.0545 0.6394 1.0000 4.500 0.5485 0.04061 0.03445 -0.0549 0.6375 1.0000 4.750 0.5811 0.04057 0.03443 -0.0556 0.6362 1.0000 5.000 0.6158 0.04041 0.03430 -0.0564 0.6353 1.0000 5.250 0.6096 0.04207 0.03598 -0.0538 0.6242 1.0000 5.500 0.6430 0.04190 0.03587 -0.0545 0.6227 1.0000 5.750 0.6777 0.04167 0.03568 -0.0553 0.6217 1.0000 6.000 0.6752 0.04333 0.03738 -0.0531 0.6108 1.0000 6.250 0.7077 0.04315 0.03726 -0.0537 0.6092 1.0000 6.500 0.7137 0.04453 0.03869 -0.0524 0.6004 1.0000 6.750 0.7402 0.04469 0.03894 -0.0526 0.5973 1.0000 7.000 0.7740 0.04433 0.03867 -0.0531 0.5956 1.0000 7.250 0.8072 0.04404 0.03848 -0.0538 0.5943 1.0000 7.500 0.8453 0.04312 0.03770 -0.0545 0.5929 1.0000 8.000 0.9818 0.03205 0.02696 -0.0570 0.5811 1.0000 8.250 1.0529 0.02278 0.01654 -0.0543 0.3889 1.0000 8.500 1.0294 0.02584 0.01911 -0.0497 0.3146 1.0000 8.750 0.9992 0.02961 0.02225 -0.0448 0.2197 1.0000 9.000 0.9682 0.03365 0.02552 -0.0404 0.1082 1.0000 9.250 0.9514 0.03708 0.02848 -0.0371 0.0492 1.0000 9.500 0.9562 0.03896 0.03040 -0.0356 0.0413 1.0000 9.750 0.9617 0.04084 0.03234 -0.0343 0.0379 1.0000 10.000 0.9612 0.04328 0.03487 -0.0326 0.0351 1.0000 10.250 0.9667 0.04523 0.03691 -0.0312 0.0329 1.0000 10.500 0.9743 0.04696 0.03870 -0.0301 0.0317 1.0000 10.750 0.9824 0.04864 0.04043 -0.0289 0.0306 1.0000 11.000 0.9883 0.05040 0.04212 -0.0274 0.0274 1.0000 11.250 1.0030 0.05120 0.04289 -0.0252 0.0263 1.0000 11.500 1.0238 0.05173 0.04346 -0.0241 0.0260 1.0000 11.750 1.0488 0.05210 0.04392 -0.0229 0.0255 1.0000 12.000 1.0858 0.05214 0.04406 -0.0217 0.0253 1.0000 12.250 1.1299 0.05281 0.04488 -0.0212 0.0252 1.0000 12.500 1.1737 0.05458 0.04689 -0.0211 0.0254 1.0000 12.750 1.1791 0.05636 0.04890 -0.0198 0.0239 1.0000