XFOIL Version 6.96 Calculated polar for: S8066 (10% version of S8065 w/ lower surface aer 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.750 -0.4633 0.09220 0.08769 -0.0311 1.0000 0.1259 -9.500 -0.4289 0.08885 0.08429 -0.0263 1.0000 0.1333 -9.250 -0.4510 0.08409 0.07962 -0.0303 1.0000 0.1389 -9.000 -0.4813 0.07837 0.07400 -0.0358 1.0000 0.1398 -8.750 -0.5178 0.07280 0.06848 -0.0404 1.0000 0.1400 -7.500 -0.6584 0.05011 0.04406 -0.0352 1.0000 0.0581 -7.250 -0.6558 0.04607 0.03996 -0.0328 1.0000 0.0556 -7.000 -0.6553 0.04245 0.03603 -0.0296 1.0000 0.0531 -6.750 -0.6522 0.03893 0.03206 -0.0264 1.0000 0.0516 -6.500 -0.6445 0.03595 0.02863 -0.0236 1.0000 0.0512 -6.250 -0.6331 0.03341 0.02571 -0.0211 1.0000 0.0519 -6.000 -0.6189 0.03086 0.02275 -0.0188 1.0000 0.0526 -5.750 -0.6018 0.02845 0.01992 -0.0167 1.0000 0.0527 -5.500 -0.5824 0.02634 0.01748 -0.0149 1.0000 0.0544 -5.250 -0.5614 0.02453 0.01533 -0.0131 1.0000 0.0578 -5.000 -0.5419 0.02272 0.01353 -0.0117 1.0000 0.0647 -4.750 -0.5226 0.02127 0.01206 -0.0101 1.0000 0.0774 -4.500 -0.5040 0.01993 0.01078 -0.0084 1.0000 0.1010 -4.250 -0.4864 0.01874 0.00979 -0.0069 1.0000 0.1375 -4.000 -0.4698 0.01733 0.00878 -0.0052 1.0000 0.1904 -3.750 -0.4572 0.01533 0.00796 -0.0032 1.0000 0.3575 -3.500 -0.4481 0.01424 0.00802 0.0008 1.0000 0.5958 -3.250 -0.4360 0.01424 0.00834 0.0051 1.0000 0.7024 -3.000 -0.4230 0.01441 0.00853 0.0089 1.0000 0.7650 -2.750 -0.4104 0.01458 0.00866 0.0129 1.0000 0.8122 -2.500 -0.3975 0.01475 0.00879 0.0169 1.0000 0.8531 -2.250 -0.3790 0.01496 0.00894 0.0198 1.0000 0.8927 -2.000 -0.3401 0.01540 0.00920 0.0187 1.0000 0.9314 -1.750 -0.2612 0.01621 0.00971 0.0097 1.0000 0.9611 -1.500 -0.1666 0.01683 0.01000 -0.0030 1.0000 0.9838 -1.250 -0.0870 0.01695 0.00989 -0.0139 1.0000 1.0000 -1.000 -0.0951 0.01668 0.00958 -0.0097 1.0000 1.0000 -0.750 -0.1033 0.01640 0.00926 -0.0052 1.0000 1.0000 -0.500 -0.1103 0.01614 0.00895 -0.0009 1.0000 1.0000 -0.250 -0.0859 0.01629 0.00902 -0.0020 0.9955 1.0000 0.000 -0.0447 0.01665 0.00930 -0.0059 0.9870 1.0000 0.250 -0.0047 0.01703 0.00959 -0.0095 0.9782 1.0000 0.500 0.0395 0.01749 0.01001 -0.0138 0.9704 1.0000 0.750 0.0742 0.01777 0.01025 -0.0161 0.9600 1.0000 1.000 0.1113 0.01810 0.01057 -0.0188 0.9500 1.0000 1.250 0.1592 0.01851 0.01099 -0.0233 0.9421 1.0000 1.500 0.1938 0.01875 0.01125 -0.0253 0.9305 1.0000 1.750 0.2295 0.01900 0.01155 -0.0273 0.9190 1.0000 2.000 0.2692 0.01921 0.01183 -0.0299 0.9077 1.0000 2.250 0.3195 0.01931 0.01203 -0.0342 0.8975 1.0000 2.500 0.3754 0.01920 0.01210 -0.0393 0.8869 1.0000 2.750 0.4257 0.01891 0.01197 -0.0428 0.8735 1.0000 3.000 0.4762 0.01832 0.01158 -0.0458 0.8588 1.0000 3.250 0.5182 0.01756 0.01099 -0.0467 0.8413 1.0000 3.500 0.5455 0.01691 0.01047 -0.0449 0.8199 1.0000 3.750 0.5775 0.01599 0.00970 -0.0435 0.7989 1.0000 4.000 0.6002 0.01532 0.00914 -0.0408 0.7735 1.0000 4.250 0.6228 0.01469 0.00858 -0.0380 0.7435 1.0000 4.500 0.6429 0.01427 0.00821 -0.0350 0.7037 1.0000 4.750 0.6627 0.01402 0.00793 -0.0320 0.6472 1.0000 5.000 0.6784 0.01415 0.00773 -0.0283 0.5482 1.0000 5.250 0.6820 0.01540 0.00791 -0.0232 0.3610 1.0000 5.500 0.6833 0.01752 0.00888 -0.0191 0.2182 1.0000 5.750 0.6957 0.01908 0.01000 -0.0165 0.1672 1.0000 6.000 0.7126 0.02046 0.01118 -0.0147 0.1406 1.0000 6.250 0.7323 0.02182 0.01236 -0.0134 0.1215 1.0000 6.500 0.7558 0.02341 0.01389 -0.0126 0.1079 1.0000 6.750 0.7790 0.02495 0.01543 -0.0118 0.0946 1.0000 7.000 0.8020 0.02656 0.01716 -0.0109 0.0826 1.0000 7.250 0.8245 0.02846 0.01921 -0.0100 0.0717 1.0000 7.500 0.8478 0.03120 0.02206 -0.0093 0.0648 1.0000 7.750 0.8680 0.03353 0.02485 -0.0076 0.0598 1.0000 8.000 0.8875 0.03615 0.02748 -0.0070 0.0547 1.0000 8.250 0.9007 0.03959 0.03146 -0.0049 0.0530 1.0000 8.500 0.9117 0.04309 0.03548 -0.0026 0.0526 1.0000 8.750 0.9190 0.04711 0.03996 -0.0003 0.0528 1.0000 9.000 0.9243 0.05174 0.04492 0.0016 0.0535 1.0000 9.250 0.9128 0.05607 0.05013 0.0061 0.0578 1.0000 9.500 0.8961 0.06182 0.05632 0.0089 0.0621 1.0000 9.750 0.8988 0.06732 0.06187 0.0097 0.0653 1.0000 10.000 0.7935 0.06048 0.05563 0.0176 0.0636 1.0000 10.250 0.7780 0.06579 0.06110 0.0182 0.0684 1.0000 10.500 0.7355 0.07175 0.06723 0.0168 0.0692 1.0000 10.750 0.6838 0.08146 0.07702 0.0107 0.0706 1.0000