XFOIL Version 6.96 Calculated polar for: FX 73-K-170/22 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.250 -0.3336 0.04876 0.04548 -0.1420 0.7852 0.0092 -12.000 -0.3333 0.04450 0.04101 -0.1474 0.7833 0.0090 -11.750 -0.3501 0.03924 0.03556 -0.1516 0.7817 0.0090 -11.500 -0.3536 0.03540 0.03161 -0.1538 0.7798 0.0086 -11.250 -0.3425 0.03414 0.03019 -0.1561 0.7778 0.0090 -11.000 -0.3370 0.03186 0.02775 -0.1578 0.7757 0.0089 -10.750 -0.3461 0.02728 0.02290 -0.1586 0.7735 0.0087 -10.250 -0.3302 0.02440 0.01967 -0.1577 0.7691 0.0087 -10.000 -0.3199 0.02387 0.01899 -0.1563 0.7673 0.0089 -9.750 -0.3113 0.02204 0.01698 -0.1547 0.7656 0.0089 -9.500 -0.2975 0.02066 0.01546 -0.1535 0.7638 0.0089 -9.250 -0.2841 0.01885 0.01346 -0.1522 0.7619 0.0090 -9.000 -0.2707 0.01725 0.01178 -0.1508 0.7600 0.0096 -8.750 -0.2526 0.01637 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0.1378 0.7642 11.000 1.3743 0.03058 0.02450 -0.0901 0.1154 0.7755 11.250 1.3770 0.03283 0.02664 -0.0889 0.0881 0.7917 11.500 1.3863 0.03474 0.02856 -0.0886 0.0697 0.8186 11.750 1.4112 0.03694 0.03096 -0.0919 0.0513 0.9360 12.000 1.4226 0.03891 0.03288 -0.0915 0.0415 1.0000 12.250 1.4288 0.04070 0.03464 -0.0902 0.0351 1.0000 12.500 1.4373 0.04231 0.03626 -0.0892 0.0310 1.0000 12.750 1.4447 0.04403 0.03799 -0.0881 0.0272 1.0000 13.000 1.4534 0.04567 0.03965 -0.0872 0.0251 1.0000 13.250 1.4599 0.04753 0.04152 -0.0861 0.0218 1.0000 13.500 1.4691 0.04919 0.04322 -0.0853 0.0205 1.0000 13.750 1.4761 0.05102 0.04507 -0.0844 0.0186 1.0000 14.000 1.4825 0.05297 0.04705 -0.0836 0.0168 1.0000 14.250 1.4905 0.05475 0.04887 -0.0828 0.0152 1.0000 14.500 1.4949 0.05695 0.05109 -0.0819 0.0135 1.0000 14.750 1.5022 0.05887 0.05306 -0.0812 0.0122 1.0000 15.000 1.5051 0.06126 0.05547 -0.0804 0.0105 1.0000 15.250 1.5101 0.06346 0.05772 -0.0797 0.0099 1.0000 15.500 1.5148 0.06572 0.06004 -0.0791 0.0090 1.0000 15.750 1.5193 0.06800 0.06237 -0.0785 0.0084 1.0000 16.000 1.5182 0.07098 0.06540 -0.0777 0.0075 1.0000 16.250 1.5239 0.07321 0.06770 -0.0773 0.0070 1.0000 16.500 1.5269 0.07578 0.07033 -0.0769 0.0067 1.0000 16.750 1.5289 0.07846 0.07308 -0.0765 0.0064 1.0000 17.000 1.5295 0.08135 0.07603 -0.0762 0.0060 1.0000 17.250 1.5272 0.08465 0.07941 -0.0758 0.0057 1.0000 17.500 1.5231 0.08825 0.08311 -0.0756 0.0054 1.0000