XFOIL Version 6.96 Calculated polar for: FX 78-K-161 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 ------ -------- --------- --------- -------- -------- -------- -12.250 -0.2115 0.10934 0.10576 -0.0633 0.7961 0.0665 -12.000 -0.2310 0.10434 0.10079 -0.0681 0.7956 0.0703 -11.750 -0.2542 0.09842 0.09491 -0.0733 0.7951 0.0710 -11.500 -0.2290 0.09599 0.09246 -0.0699 0.7935 0.0741 -11.250 -0.2218 0.09346 0.08992 -0.0699 0.7922 0.0763 -11.000 -0.2234 0.08983 0.08628 -0.0711 0.7912 0.0788 -10.750 -0.2343 0.08499 0.08146 -0.0734 0.7905 0.0815 -10.500 -0.2715 0.07641 0.07293 -0.0804 0.7901 0.0837 -10.250 -0.3514 0.07694 0.07321 -0.0903 0.7931 0.0767 -10.000 -0.3760 0.07255 0.06878 -0.0912 0.7916 0.0774 -9.750 -0.4009 0.06917 0.06533 -0.0899 0.7902 0.0784 -9.500 -0.5554 0.05452 0.04959 -0.0756 0.7883 0.0493 -9.250 -0.5489 0.05201 0.04703 -0.0743 0.7863 0.0500 -9.000 -0.5348 0.05404 0.04914 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5.500 0.9113 0.03066 0.02536 -0.0655 0.6181 1.0000 5.750 0.9411 0.02957 0.02436 -0.0648 0.6167 1.0000 6.000 0.9913 0.02609 0.02093 -0.0652 0.6170 1.0000 6.250 0.9944 0.02680 0.02175 -0.0624 0.6047 1.0000 6.500 1.0733 0.02009 0.01501 -0.0646 0.6026 1.0000 6.750 1.1023 0.01834 0.01328 -0.0635 0.5847 1.0000 7.000 1.1224 0.01784 0.01282 -0.0619 0.5660 1.0000 7.250 1.1385 0.01743 0.01232 -0.0596 0.5232 1.0000 7.500 1.1305 0.01809 0.01225 -0.0535 0.4218 1.0000 7.750 1.1107 0.01967 0.01354 -0.0471 0.3725 1.0000 8.000 1.0902 0.02073 0.01456 -0.0402 0.3543 1.0000 8.250 1.0608 0.02178 0.01557 -0.0320 0.3401 1.0000 8.500 1.0292 0.02312 0.01676 -0.0240 0.3162 1.0000 8.750 1.0118 0.02413 0.01770 -0.0180 0.2981 1.0000 9.000 0.9799 0.02567 0.01901 -0.0104 0.2618 1.0000 9.250 0.9456 0.02733 0.02040 -0.0027 0.2197 1.0000 9.500 0.9129 0.02909 0.02185 0.0044 0.1761 1.0000 9.750 0.8956 0.03086 0.02336 0.0088 0.1344 1.0000 10.000 0.8714 0.03372 0.02570 0.0129 0.0666 1.0000 10.250 0.8653 0.03584 0.02764 0.0153 0.0444 1.0000 10.500 0.8661 0.03769 0.02946 0.0169 0.0375 1.0000 10.750 0.8703 0.03942 0.03125 0.0182 0.0337 1.0000 11.000 0.8762 0.04109 0.03298 0.0191 0.0326 1.0000 11.250 0.8776 0.04323 0.03518 0.0201 0.0310 1.0000 11.500 0.8841 0.04500 0.03704 0.0208 0.0302 1.0000 11.750 0.8886 0.04699 0.03909 0.0217 0.0286 1.0000 12.000 0.8962 0.04869 0.04085 0.0223 0.0285 1.0000 12.250 0.9043 0.05035 0.04255 0.0230 0.0281 1.0000 12.500 0.9128 0.05195 0.04415 0.0238 0.0271 1.0000 12.750 0.9231 0.05334 0.04552 0.0245 0.0261 1.0000 13.000 0.9397 0.05395 0.04608 0.0260 0.0255 1.0000 13.250 0.9555 0.05497 0.04717 0.0266 0.0248 1.0000 13.500 0.9744 0.05576 0.04803 0.0275 0.0242 1.0000 13.750 0.9987 0.05620 0.04852 0.0286 0.0243 1.0000 14.000 1.0190 0.05719 0.04964 0.0294 0.0240 1.0000 14.250 1.0419 0.05826 0.05086 0.0302 0.0240 1.0000 14.500 1.0618 0.05988 0.05267 0.0310 0.0240 1.0000 14.750 1.0848 0.06164 0.05456 0.0315 0.0246 1.0000 15.000 1.0976 0.06418 0.05731 0.0321 0.0247 1.0000 15.250 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