XFOIL Version 6.96 Calculated polar for: SIKORSKY SC1095 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.000 -0.5500 0.09514 0.08809 0.0291 1.0000 0.4030 -7.750 -0.5442 0.09198 0.08494 0.0298 1.0000 0.4221 -7.500 -0.6722 0.06493 0.05769 -0.0154 1.0000 0.1985 -7.250 -0.6566 0.06007 0.05275 -0.0155 1.0000 0.1948 -7.000 -0.6490 0.05469 0.04708 -0.0170 1.0000 0.1929 -6.750 -0.6385 0.04963 0.04158 -0.0181 1.0000 0.1919 -6.500 -0.6244 0.04497 0.03644 -0.0187 1.0000 0.1912 -6.250 -0.6073 0.04111 0.03204 -0.0188 1.0000 0.1941 -6.000 -0.5881 0.03809 0.02865 -0.0184 1.0000 0.2017 -5.750 -0.5666 0.03552 0.02571 -0.0179 1.0000 0.2099 -5.500 -0.5441 0.03316 0.02312 -0.0174 1.0000 0.2191 -5.250 -0.5213 0.03115 0.02078 -0.0168 1.0000 0.2316 -5.000 -0.4977 0.02942 0.01880 -0.0161 1.0000 0.2450 -4.750 -0.4736 0.02789 0.01705 -0.0155 1.0000 0.2588 -4.500 -0.4494 0.02645 0.01556 -0.0147 1.0000 0.2733 -4.250 -0.4249 0.02512 0.01415 -0.0140 1.0000 0.2885 -4.000 -0.3997 0.02385 0.01284 -0.0133 1.0000 0.3035 -3.750 -0.3754 0.02271 0.01182 -0.0124 1.0000 0.3242 -3.500 -0.3501 0.02164 0.01079 -0.0116 1.0000 0.3505 -3.250 -0.3254 0.02048 0.00988 -0.0107 1.0000 0.3857 -3.000 -0.3037 0.01914 0.00908 -0.0092 1.0000 0.4569 -2.750 -0.2942 0.01738 0.00897 -0.0032 1.0000 0.6685 -2.500 -0.1994 0.01839 0.00993 -0.0063 1.0000 0.9546 -2.250 -0.0892 0.01797 0.00883 -0.0221 1.0000 1.0000 -2.000 -0.0773 0.01759 0.00834 -0.0207 1.0000 1.0000 -1.750 -0.0669 0.01732 0.00797 -0.0188 1.0000 1.0000 -1.500 -0.0586 0.01713 0.00770 -0.0163 1.0000 1.0000 -1.250 -0.0515 0.01701 0.00750 -0.0135 1.0000 1.0000 -1.000 -0.0444 0.01694 0.00735 -0.0106 1.0000 1.0000 -0.750 -0.0367 0.01693 0.00726 -0.0078 1.0000 1.0000 -0.500 -0.0275 0.01697 0.00723 -0.0053 1.0000 1.0000 -0.250 -0.0158 0.01707 0.00725 -0.0032 1.0000 1.0000 0.000 -0.0018 0.01722 0.00733 -0.0015 1.0000 1.0000 0.250 0.0138 0.01743 0.00748 -0.0003 1.0000 1.0000 0.500 0.0306 0.01769 0.00770 0.0007 1.0000 1.0000 0.750 0.0479 0.01801 0.00800 0.0015 1.0000 1.0000 1.000 0.0656 0.01841 0.00840 0.0020 1.0000 1.0000 1.250 0.0832 0.01891 0.00890 0.0023 1.0000 1.0000 1.500 0.1004 0.01951 0.00953 0.0023 1.0000 1.0000 1.750 0.1167 0.02027 0.01033 0.0021 1.0000 1.0000 2.000 0.2211 0.02132 0.01162 -0.0134 0.9596 1.0000 2.250 0.3282 0.02118 0.01184 -0.0268 0.9049 1.0000 2.500 0.3969 0.02041 0.01131 -0.0310 0.8510 1.0000 2.750 0.4346 0.01973 0.01072 -0.0290 0.7948 1.0000 3.000 0.4581 0.01934 0.01022 -0.0248 0.7330 1.0000 3.250 0.4773 0.01932 0.00995 -0.0205 0.6632 1.0000 3.500 0.4965 0.01967 0.00988 -0.0167 0.5921 1.0000 3.750 0.5169 0.02041 0.01019 -0.0140 0.5236 1.0000 4.000 0.5388 0.02140 0.01077 -0.0121 0.4639 1.0000 4.250 0.5620 0.02251 0.01156 -0.0107 0.4170 1.0000 4.500 0.5861 0.02367 0.01249 -0.0096 0.3808 1.0000 4.750 0.6111 0.02488 0.01354 -0.0088 0.3530 1.0000 5.000 0.6356 0.02610 0.01480 -0.0082 0.3283 1.0000 5.250 0.6608 0.02741 0.01607 -0.0076 0.3099 1.0000 5.500 0.6861 0.02890 0.01769 -0.0072 0.2954 1.0000 5.750 0.7107 0.03045 0.01937 -0.0067 0.2820 1.0000 6.000 0.7345 0.03206 0.02114 -0.0062 0.2698 1.0000 6.250 0.7594 0.03374 0.02280 -0.0058 0.2612 1.0000 6.500 0.7807 0.03615 0.02576 -0.0055 0.2542 1.0000 6.750 0.8048 0.03803 0.02768 -0.0051 0.2475 1.0000 7.000 0.8218 0.04088 0.03107 -0.0048 0.2409 1.0000 7.250 0.8417 0.04322 0.03363 -0.0043 0.2347 1.0000 7.500 0.8619 0.04604 0.03659 -0.0040 0.2314 1.0000 7.750 0.8712 0.05041 0.04156 -0.0040 0.2302 1.0000 8.000 0.8763 0.05532 0.04694 -0.0044 0.2297 1.0000 8.250 0.8756 0.06082 0.05282 -0.0053 0.2294 1.0000 8.500 0.8698 0.06686 0.05914 -0.0067 0.2298 1.0000 8.750 0.8611 0.07347 0.06595 -0.0088 0.2326 1.0000