XFOIL Version 6.96 Calculated polar for: SIKORSKY SC1094R8 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -7.750 -0.5035 0.10118 0.09615 -0.0082 1.0000 0.0632 -7.500 -0.5110 0.09631 0.09133 -0.0153 1.0000 0.0637 -7.250 -0.5173 0.09118 0.08619 -0.0220 1.0000 0.0639 -7.000 -0.5181 0.08648 0.08140 -0.0263 1.0000 0.0640 -6.750 -0.5128 0.08176 0.07669 -0.0278 1.0000 0.0642 -6.500 -0.5006 0.07792 0.07294 -0.0264 1.0000 0.0649 -6.000 -0.4790 0.07198 0.06706 -0.0254 1.0000 0.0677 -5.500 -0.4736 0.05354 0.04767 -0.0335 1.0000 0.0392 -5.250 -0.4597 0.05064 0.04471 -0.0331 1.0000 0.0388 -5.000 -0.4458 0.04750 0.04143 -0.0327 1.0000 0.0383 -4.750 -0.4314 0.04422 0.03794 -0.0321 1.0000 0.0378 -4.500 -0.4164 0.04098 0.03446 -0.0312 1.0000 0.0374 -4.250 -0.4008 0.03789 0.03108 -0.0300 1.0000 0.0370 -4.000 -0.3843 0.03502 0.02787 -0.0286 1.0000 0.0368 -3.750 -0.3666 0.03242 0.02493 -0.0271 1.0000 0.0368 -3.500 -0.3478 0.03019 0.02235 -0.0256 1.0000 0.0373 -3.250 -0.3281 0.02817 0.01990 -0.0241 1.0000 0.0385 -3.000 -0.3074 0.02640 0.01772 -0.0225 1.0000 0.0394 -2.750 -0.2869 0.02502 0.01623 -0.0212 1.0000 0.0400 -2.500 -0.2657 0.02382 0.01491 -0.0199 1.0000 0.0406 -2.250 -0.2440 0.02276 0.01375 -0.0187 1.0000 0.0413 -2.000 -0.2049 0.02150 0.01234 -0.0204 0.9940 0.0426 -1.750 -0.1604 0.02038 0.01103 -0.0230 0.9849 0.0455 -1.500 -0.1157 0.01933 0.01002 -0.0258 0.9751 0.0484 -1.250 -0.0738 0.01840 0.00909 -0.0279 0.9652 0.0512 -1.000 -0.0370 0.01763 0.00832 -0.0290 0.9538 0.0550 -0.750 -0.0029 0.01701 0.00780 -0.0297 0.9410 0.0606 -0.500 0.0300 0.01639 0.00720 -0.0300 0.9272 0.0663 -0.250 0.0617 0.01588 0.00674 -0.0299 0.9117 0.0774 0.000 0.0920 0.01534 0.00629 -0.0296 0.8945 0.0975 0.250 0.1203 0.01456 0.00589 -0.0289 0.8733 0.1774 0.500 0.1301 0.01227 0.00603 -0.0235 0.8512 0.8264 0.750 0.1965 0.01208 0.00578 -0.0274 0.8124 0.9928 1.000 0.2279 0.01202 0.00546 -0.0271 0.7722 1.0000 1.250 0.2500 0.01203 0.00521 -0.0251 0.7307 1.0000 1.500 0.2721 0.01211 0.00500 -0.0232 0.6823 1.0000 1.750 0.2945 0.01226 0.00482 -0.0213 0.6278 1.0000 2.000 0.3169 0.01251 0.00470 -0.0196 0.5704 1.0000 2.250 0.3395 0.01283 0.00464 -0.0181 0.5144 1.0000 2.500 0.3626 0.01319 0.00465 -0.0168 0.4641 1.0000 2.750 0.3861 0.01356 0.00471 -0.0156 0.4193 1.0000 3.000 0.4100 0.01395 0.00480 -0.0146 0.3803 1.0000 3.250 0.4343 0.01434 0.00494 -0.0136 0.3464 1.0000 3.500 0.4589 0.01472 0.00510 -0.0128 0.3153 1.0000 3.750 0.4838 0.01511 0.00529 -0.0119 0.2876 1.0000 4.000 0.5086 0.01552 0.00550 -0.0111 0.2630 1.0000 4.250 0.5338 0.01592 0.00574 -0.0104 0.2413 1.0000 4.500 0.5589 0.01634 0.00601 -0.0096 0.2234 1.0000 4.750 0.5840 0.01678 0.00632 -0.0088 0.2093 1.0000 5.000 0.6089 0.01726 0.00665 -0.0081 0.1976 1.0000 5.250 0.6342 0.01771 0.00704 -0.0074 0.1869 1.0000 5.500 0.6592 0.01821 0.00744 -0.0066 0.1782 1.0000 5.750 0.6843 0.01871 0.00788 -0.0059 0.1706 1.0000 6.000 0.7090 0.01928 0.00837 -0.0051 0.1648 1.0000 6.250 0.7343 0.01980 0.00889 -0.0044 0.1589 1.0000 6.500 0.7589 0.02038 0.00941 -0.0036 0.1538 1.0000 6.750 0.7837 0.02099 0.00999 -0.0029 0.1491 1.0000 7.000 0.8088 0.02156 0.01060 -0.0021 0.1443 1.0000 7.250 0.8334 0.02218 0.01119 -0.0014 0.1405 1.0000 7.500 0.8577 0.02293 0.01186 -0.0007 0.1375 1.0000 7.750 0.8826 0.02364 0.01266 0.0001 0.1347 1.0000 8.000 0.9072 0.02437 0.01347 0.0008 0.1316 1.0000 8.250 0.9316 0.02510 0.01426 0.0015 0.1286 1.0000 8.500 0.9556 0.02583 0.01499 0.0023 0.1259 1.0000 8.750 0.9794 0.02666 0.01577 0.0030 0.1236 1.0000 9.000 1.0031 0.02759 0.01681 0.0037 0.1214 1.0000 9.250 1.0265 0.02856 0.01798 0.0045 0.1194 1.0000 9.500 1.0494 0.02959 0.01915 0.0053 0.1174 1.0000 9.750 1.0719 0.03064 0.02033 0.0061 0.1156 1.0000 10.000 1.0941 0.03169 0.02150 0.0069 0.1139 1.0000 10.250 1.1161 0.03271 0.02259 0.0077 0.1123 1.0000 10.500 1.1381 0.03376 0.02366 0.0085 0.1108 1.0000 10.750 1.1592 0.03507 0.02502 0.0092 0.1094 1.0000 11.000 1.1765 0.03658 0.02687 0.0103 0.1079 1.0000 11.250 1.1928 0.03826 0.02885 0.0114 0.1065 1.0000 11.500 1.2075 0.04008 0.03095 0.0126 0.1052 1.0000 11.750 1.2208 0.04199 0.03314 0.0137 0.1039 1.0000 12.000 1.2323 0.04398 0.03539 0.0149 0.1028 1.0000 12.250 1.2424 0.04598 0.03761 0.0162 0.1017 1.0000 12.500 1.2516 0.04790 0.03973 0.0174 0.1006 1.0000 12.750 1.2606 0.04972 0.04171 0.0187 0.0996 1.0000 13.000 1.2693 0.05151 0.04361 0.0199 0.0986 1.0000 13.250 1.2782 0.05336 0.04555 0.0210 0.0978 1.0000 13.500 1.2783 0.05589 0.04822 0.0224 0.0970 1.0000 13.750 1.2499 0.06011 0.05279 0.0239 0.0967 1.0000 14.000 1.2082 0.06650 0.05954 0.0226 0.0964 1.0000