XFOIL Version 6.96 Calculated polar for: FX 68-H-120 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 ------ -------- --------- --------- -------- -------- -------- -10.250 -0.4835 0.08194 0.07890 -0.0358 1.0000 0.0334 -10.000 -0.5972 0.05330 0.04992 -0.0604 1.0000 0.0249 -9.750 -0.6194 0.05029 0.04675 -0.0594 1.0000 0.0248 -9.500 -0.6425 0.04998 0.04636 -0.0535 1.0000 0.0245 -9.250 -0.6683 0.04882 0.04510 -0.0475 1.0000 0.0245 -9.000 -0.6836 0.04731 0.04343 -0.0429 0.9996 0.0244 -8.750 -0.6715 0.04368 0.03941 -0.0443 0.9944 0.0242 -8.500 -0.6753 0.03741 0.03258 -0.0442 0.9882 0.0249 -8.250 -0.6591 0.03391 0.02863 -0.0445 0.9845 0.0251 -8.000 -0.6449 0.03099 0.02535 -0.0437 0.9802 0.0256 -7.750 -0.6247 0.02852 0.02250 -0.0433 0.9762 0.0258 -7.500 -0.5993 0.02630 0.01995 -0.0435 0.9733 0.0262 -7.250 -0.5717 0.02447 0.01790 -0.0440 0.9712 0.0274 -7.000 -0.5545 0.02323 0.01651 -0.0423 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2.750 0.5789 0.01162 0.00424 -0.0414 0.4207 1.0000 3.000 0.6008 0.01199 0.00444 -0.0404 0.3955 1.0000 3.250 0.6228 0.01233 0.00466 -0.0395 0.3728 1.0000 3.500 0.6445 0.01271 0.00489 -0.0385 0.3530 1.0000 3.750 0.6661 0.01308 0.00515 -0.0375 0.3347 1.0000 4.000 0.6878 0.01344 0.00542 -0.0365 0.3177 1.0000 4.250 0.7093 0.01381 0.00570 -0.0354 0.3027 1.0000 4.500 0.7307 0.01420 0.00600 -0.0344 0.2897 1.0000 4.750 0.7519 0.01462 0.00633 -0.0333 0.2788 1.0000 5.000 0.7737 0.01497 0.00667 -0.0322 0.2686 1.0000 5.250 0.7953 0.01538 0.00704 -0.0312 0.2599 1.0000 5.500 0.8167 0.01583 0.00741 -0.0301 0.2525 1.0000 5.750 0.8388 0.01622 0.00785 -0.0291 0.2455 1.0000 6.000 0.8605 0.01666 0.00824 -0.0282 0.2395 1.0000 6.250 0.8826 0.01712 0.00872 -0.0272 0.2340 1.0000 6.500 0.9041 0.01748 0.00910 -0.0262 0.2276 1.0000 6.750 0.9247 0.01787 0.00948 -0.0251 0.2204 1.0000 7.000 0.9439 0.01808 0.00969 -0.0237 0.2112 1.0000 7.250 0.9630 0.01828 0.00999 -0.0224 0.2017 1.0000 7.500 0.9820 0.01865 0.01032 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1.0738 0.05227 0.04549 0.0167 0.0165 1.0000 13.000 1.0691 0.05585 0.04916 0.0162 0.0166 1.0000 13.250 1.0669 0.05922 0.05263 0.0156 0.0168 1.0000 13.500 1.0659 0.06247 0.05595 0.0153 0.0170 1.0000 13.750 1.0662 0.06550 0.05905 0.0153 0.0170 1.0000 14.000 1.0688 0.06827 0.06189 0.0153 0.0172 1.0000 14.250 1.0744 0.07055 0.06422 0.0159 0.0175 1.0000 14.500 1.0831 0.07241 0.06614 0.0171 0.0179 1.0000 14.750 1.0890 0.07486 0.06867 0.0176 0.0183 1.0000 15.000 1.0965 0.07724 0.07114 0.0186 0.0188 1.0000 15.250 1.1248 0.07765 0.07156 0.0226 0.0200 1.0000 15.500 1.1224 0.08106 0.07510 0.0210 0.0203 1.0000 15.750 1.1172 0.08512 0.07934 0.0189 0.0207 1.0000 16.000 1.1093 0.08994 0.08438 0.0162 0.0213 1.0000 16.250 1.0987 0.09573 0.09048 0.0132 0.0225 1.0000 16.500 1.0841 0.10229 0.09729 0.0097 0.0233 1.0000 16.750 1.0694 0.10912 0.10436 0.0062 0.0244 1.0000 17.000 1.0556 0.11587 0.11129 0.0025 0.0249 1.0000 17.250 1.0392 0.12336 0.11895 -0.0017 0.0255 1.0000 17.500 1.0235 0.13091 0.12665 -0.0062 0.0258 1.0000 17.750 1.0049 0.13940 0.13529 -0.0114 0.0261 1.0000 18.000 0.9850 0.14860 0.14464 -0.0172 0.0263 1.0000 18.250 0.9623 0.15908 0.15524 -0.0237 0.0265 1.0000 18.500 0.9378 0.17072 0.16699 -0.0309 0.0266 1.0000 18.750 0.7331 0.15966 0.15644 -0.0260 0.0232 1.0000