XFOIL Version 6.96 Calculated polar for: FX 61-168 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.250 -0.7599 0.08765 0.08539 -0.0560 1.0000 0.0032 -16.000 -0.7921 0.07724 0.07481 -0.0620 1.0000 0.0033 -15.750 -0.8105 0.07016 0.06760 -0.0660 1.0000 0.0034 -15.500 -0.8474 0.06092 0.05810 -0.0709 1.0000 0.0032 -15.250 -0.8572 0.05638 0.05344 -0.0728 1.0000 0.0033 -15.000 -0.8599 0.05307 0.05005 -0.0740 1.0000 0.0033 -14.750 -0.8723 0.04878 0.04561 -0.0751 1.0000 0.0033 -14.500 -0.8791 0.04552 0.04223 -0.0756 1.0000 0.0034 -14.250 -0.8843 0.04268 0.03927 -0.0756 1.0000 0.0034 -14.000 -0.8812 0.04018 0.03666 -0.0764 0.9997 0.0035 -13.750 -0.8694 0.03747 0.03381 -0.0791 0.9986 0.0035 -13.500 -0.8583 0.03489 0.03110 -0.0813 0.9969 0.0035 -13.250 -0.8496 0.03260 0.02867 -0.0824 0.9943 0.0036 -13.000 -0.8289 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0.6744 7.000 1.2932 0.01212 0.00582 -0.1192 0.2321 0.6760 7.250 1.3089 0.01281 0.00634 -0.1173 0.1994 0.6776 7.500 1.3222 0.01359 0.00693 -0.1151 0.1676 0.6792 7.750 1.3334 0.01437 0.00754 -0.1124 0.1368 0.6807 8.000 1.3421 0.01508 0.00812 -0.1093 0.1135 0.6819 8.250 1.3524 0.01577 0.00872 -0.1065 0.0937 0.6835 8.500 1.3608 0.01654 0.00942 -0.1035 0.0755 0.6851 8.750 1.3684 0.01736 0.01016 -0.1005 0.0585 0.6866 9.000 1.3770 0.01815 0.01092 -0.0977 0.0462 0.6881 9.500 1.3897 0.02005 0.01275 -0.0920 0.0266 0.6910 9.750 1.3985 0.02094 0.01366 -0.0897 0.0214 0.6926 10.000 1.4059 0.02198 0.01470 -0.0875 0.0170 0.6942 10.250 1.4119 0.02316 0.01590 -0.0853 0.0129 0.6957 10.500 1.4164 0.02454 0.01729 -0.0831 0.0086 0.6969 10.750 1.4157 0.02640 0.01917 -0.0808 0.0030 0.6983 11.000 1.4224 0.02787 0.02070 -0.0794 0.0025 0.6997 11.250 1.4293 0.02942 0.02232 -0.0782 0.0022 0.7011 11.500 1.4358 0.03108 0.02406 -0.0771 0.0019 0.7025 11.750 1.4431 0.03274 0.02578 -0.0762 0.0018 0.7040 12.000 1.4502 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0.08900 -0.0791 0.0011 0.7363 17.250 1.4832 0.09826 0.09320 -0.0805 0.0011 0.7381 17.500 1.4813 0.10252 0.09756 -0.0820 0.0010 0.7397 17.750 1.4781 0.10705 0.10219 -0.0836 0.0010 0.7413 18.250 1.4714 0.11635 0.11170 -0.0874 0.0010 0.7448 18.500 1.4665 0.12136 0.11683 -0.0897 0.0010 0.7467 18.750 1.4622 0.12628 0.12186 -0.0919 0.0010 0.7487