XFOIL Version 6.96 Calculated polar for: S1010 HPV airfoil 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.250 -0.6956 0.08977 0.08290 0.0008 1.0000 0.0477 -9.000 -0.7024 0.08373 0.07692 -0.0037 1.0000 0.0474 -8.750 -0.7118 0.07798 0.07119 -0.0071 1.0000 0.0471 -8.500 -0.7202 0.07210 0.06525 -0.0100 1.0000 0.0468 -8.250 -0.7271 0.06630 0.05931 -0.0122 1.0000 0.0468 -8.000 -0.7318 0.06047 0.05323 -0.0137 1.0000 0.0470 -7.750 -0.7338 0.05456 0.04689 -0.0146 1.0000 0.0479 -7.500 -0.7287 0.05007 0.04202 -0.0147 1.0000 0.0504 -7.250 -0.7134 0.04823 0.04009 -0.0142 1.0000 0.0551 -7.000 -0.7028 0.04366 0.03495 -0.0137 1.0000 0.0573 -6.750 -0.6888 0.03914 0.02970 -0.0130 1.0000 0.0595 -6.500 -0.6708 0.03543 0.02538 -0.0120 1.0000 0.0624 -6.250 -0.6502 0.03326 0.02302 -0.0112 1.0000 0.0669 -6.000 -0.6286 0.03116 0.02047 -0.0104 1.0000 0.0760 -5.750 -0.6060 0.02941 0.01845 -0.0096 1.0000 0.0851 -5.500 -0.5829 0.02780 0.01668 -0.0088 1.0000 0.0955 -5.250 -0.5594 0.02645 0.01505 -0.0080 1.0000 0.1094 -5.000 -0.5351 0.02510 0.01354 -0.0073 1.0000 0.1235 -4.750 -0.5105 0.02399 0.01221 -0.0065 1.0000 0.1412 -4.500 -0.4854 0.02283 0.01103 -0.0058 1.0000 0.1565 -4.250 -0.4609 0.02192 0.01010 -0.0051 1.0000 0.1782 -4.000 -0.4355 0.02097 0.00914 -0.0046 1.0000 0.2000 -3.750 -0.4109 0.02010 0.00832 -0.0040 1.0000 0.2289 -3.500 -0.3879 0.01925 0.00749 -0.0031 1.0000 0.2631 -3.250 -0.3661 0.01834 0.00683 -0.0021 1.0000 0.3100 -3.000 -0.3461 0.01732 0.00625 -0.0007 1.0000 0.3856 -2.750 -0.3299 0.01611 0.00585 0.0019 1.0000 0.5261 -2.500 -0.2998 0.01536 0.00607 0.0044 1.0000 0.7959 -2.250 -0.2438 0.01540 0.00585 0.0009 1.0000 0.9200 -2.000 -0.1644 0.01529 0.00533 -0.0087 1.0000 0.9866 -1.750 -0.1283 0.01509 0.00490 -0.0109 1.0000 1.0000 -1.500 -0.1094 0.01494 0.00461 -0.0095 1.0000 1.0000 -1.250 -0.0907 0.01482 0.00439 -0.0081 1.0000 1.0000 -1.000 -0.0721 0.01473 0.00422 -0.0066 1.0000 1.0000 -0.750 -0.0538 0.01466 0.00409 -0.0050 1.0000 1.0000 -0.500 -0.0357 0.01460 0.00399 -0.0034 1.0000 1.0000 -0.250 -0.0177 0.01457 0.00394 -0.0017 1.0000 1.0000 0.000 0.0000 0.01456 0.00392 0.0000 1.0000 1.0000 0.250 0.0177 0.01457 0.00394 0.0017 1.0000 1.0000 0.500 0.0357 0.01460 0.00399 0.0034 1.0000 1.0000 0.750 0.0538 0.01465 0.00409 0.0050 1.0000 1.0000 1.000 0.0721 0.01473 0.00422 0.0066 1.0000 1.0000 1.250 0.0907 0.01482 0.00439 0.0081 1.0000 1.0000 1.500 0.1095 0.01494 0.00461 0.0095 1.0000 1.0000 1.750 0.1284 0.01508 0.00490 0.0108 1.0000 1.0000 2.000 0.1641 0.01529 0.00532 0.0088 0.9868 1.0000 2.250 0.2439 0.01539 0.00585 -0.0009 0.9200 1.0000 2.500 0.2997 0.01536 0.00607 -0.0044 0.7963 1.0000 2.750 0.3298 0.01611 0.00585 -0.0019 0.5266 1.0000 3.000 0.3460 0.01732 0.00625 0.0007 0.3858 1.0000 3.250 0.3660 0.01834 0.00683 0.0021 0.3100 1.0000 3.500 0.3878 0.01925 0.00748 0.0031 0.2633 1.0000 3.750 0.4109 0.02010 0.00831 0.0040 0.2289 1.0000 4.000 0.4355 0.02097 0.00914 0.0046 0.2002 1.0000 4.250 0.4609 0.02192 0.01010 0.0052 0.1783 1.0000 4.500 0.4854 0.02283 0.01102 0.0058 0.1564 1.0000 4.750 0.5105 0.02399 0.01220 0.0065 0.1412 1.0000 5.000 0.5351 0.02510 0.01354 0.0073 0.1235 1.0000 5.250 0.5594 0.02646 0.01505 0.0081 0.1094 1.0000 5.500 0.5829 0.02781 0.01669 0.0088 0.0954 1.0000 5.750 0.6060 0.02941 0.01845 0.0096 0.0851 1.0000 6.000 0.6287 0.03117 0.02048 0.0104 0.0760 1.0000 6.250 0.6503 0.03326 0.02302 0.0112 0.0668 1.0000 6.500 0.6710 0.03543 0.02538 0.0120 0.0624 1.0000 6.750 0.6890 0.03916 0.02972 0.0129 0.0595 1.0000 7.000 0.7031 0.04368 0.03497 0.0137 0.0573 1.0000 7.250 0.7137 0.04826 0.04012 0.0141 0.0550 1.0000 7.500 0.7292 0.05003 0.04196 0.0147 0.0503 1.0000 7.750 0.7340 0.05464 0.04697 0.0145 0.0479 1.0000 8.000 0.7322 0.06055 0.05331 0.0136 0.0470 1.0000 8.250 0.7276 0.06637 0.05939 0.0120 0.0468 1.0000 8.500 0.7207 0.07219 0.06534 0.0098 0.0468 1.0000 8.750 0.7122 0.07812 0.07133 0.0068 0.0471 1.0000 9.000 0.7031 0.08384 0.07703 0.0034 0.0474 1.0000 9.250 0.6965 0.08987 0.08300 -0.0010 0.0477 1.0000