XFOIL Version 6.96 Calculated polar for: SIKORSKY SC2110 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.500 -0.5167 0.08672 0.08350 -0.0197 1.0000 0.0394 -8.250 -0.5255 0.08122 0.07786 -0.0276 1.0000 0.0397 -8.000 -0.5320 0.07700 0.07337 -0.0315 1.0000 0.0399 -7.750 -0.5238 0.07115 0.06766 -0.0318 1.0000 0.0407 -7.500 -0.5133 0.06835 0.06494 -0.0311 1.0000 0.0416 -7.250 -0.5095 0.06574 0.06231 -0.0305 1.0000 0.0426 -7.000 -0.5138 0.06345 0.05998 -0.0285 1.0000 0.0436 -6.750 -0.5188 0.06117 0.05763 -0.0261 1.0000 0.0447 -6.500 -0.5219 0.05876 0.05510 -0.0237 1.0000 0.0462 -6.250 -0.5258 0.05862 0.05429 -0.0203 1.0000 0.0491 -6.000 -0.5251 0.05299 0.04864 -0.0190 1.0000 0.0500 -5.750 -0.5141 0.04970 0.04543 -0.0184 0.9994 0.0510 -5.500 -0.4893 0.04673 0.04243 -0.0202 0.9966 0.0529 -5.250 -0.4606 0.04401 0.03947 -0.0220 0.9940 0.0572 -5.000 -0.4346 0.04045 0.03547 -0.0234 0.9902 0.0624 -4.750 -0.4065 0.03791 0.03291 -0.0251 0.9875 0.0656 -4.500 -0.3740 0.03561 0.03014 -0.0268 0.9849 0.0752 -4.250 -0.3485 0.03330 0.02788 -0.0277 0.9812 0.0793 -4.000 -0.3178 0.03129 0.02559 -0.0291 0.9780 0.0910 -3.750 -0.2846 0.02949 0.02360 -0.0310 0.9757 0.1056 -3.500 -0.2568 0.02786 0.02188 -0.0319 0.9719 0.1216 -3.250 -0.2272 0.02624 0.02024 -0.0330 0.9683 0.1407 -3.000 -0.1713 0.02072 0.01328 -0.0308 0.9668 0.0454 -2.750 -0.1184 0.01873 0.01102 -0.0346 0.9639 0.0428 -2.500 -0.0774 0.01752 0.00978 -0.0366 0.9561 0.0436 -2.250 -0.0339 0.01671 0.00895 -0.0392 0.9502 0.0477 -2.000 -0.0052 0.01587 0.00814 -0.0390 0.9416 0.0505 -1.750 0.0228 0.01520 0.00754 -0.0387 0.9333 0.0551 -1.500 0.0503 0.01467 0.00702 -0.0380 0.9250 0.0643 -1.250 0.0742 0.01418 0.00656 -0.0367 0.9149 0.0830 -1.000 0.0754 0.01144 0.00669 -0.0305 0.9070 0.8114 -0.750 0.0840 0.01159 0.00695 -0.0241 0.8963 0.8860 -0.500 0.0953 0.01176 0.00710 -0.0183 0.8862 0.9282 -0.250 0.1429 0.01186 0.00712 -0.0190 0.8801 0.9713 0.000 0.2077 0.01164 0.00678 -0.0251 0.8717 0.9866 0.250 0.2403 0.01128 0.00633 -0.0255 0.8619 0.9933 0.500 0.2765 0.01094 0.00593 -0.0268 0.8485 0.9990 0.750 0.2981 0.01062 0.00556 -0.0254 0.8342 1.0000 1.000 0.3173 0.01030 0.00518 -0.0235 0.8181 1.0000 1.250 0.3365 0.00998 0.00479 -0.0214 0.7995 1.0000 1.500 0.3576 0.00973 0.00449 -0.0199 0.7734 1.0000 1.750 0.3778 0.00949 0.00413 -0.0179 0.7369 1.0000 2.000 0.3974 0.00938 0.00372 -0.0157 0.6607 1.0000 2.250 0.4173 0.01012 0.00348 -0.0141 0.4818 1.0000 2.500 0.4400 0.01097 0.00371 -0.0139 0.3858 1.0000 2.750 0.4626 0.01150 0.00393 -0.0134 0.3461 1.0000 3.000 0.4854 0.01191 0.00414 -0.0128 0.3202 1.0000 3.250 0.5082 0.01230 0.00437 -0.0122 0.3002 1.0000 3.500 0.5315 0.01267 0.00460 -0.0116 0.2834 1.0000 3.750 0.5557 0.01302 0.00485 -0.0112 0.2686 1.0000 4.000 0.5807 0.01340 0.00513 -0.0109 0.2559 1.0000 4.250 0.6060 0.01382 0.00544 -0.0107 0.2449 1.0000 4.500 0.6319 0.01419 0.00573 -0.0106 0.2341 1.0000 4.750 0.6581 0.01456 0.00607 -0.0105 0.2241 1.0000 5.000 0.6840 0.01506 0.00644 -0.0104 0.2156 1.0000 5.250 0.7107 0.01540 0.00682 -0.0104 0.2072 1.0000 5.500 0.7367 0.01594 0.00726 -0.0103 0.2000 1.0000 5.750 0.7635 0.01628 0.00764 -0.0103 0.1923 1.0000 6.000 0.7894 0.01691 0.00815 -0.0103 0.1858 1.0000 6.250 0.8162 0.01728 0.00863 -0.0102 0.1797 1.0000 6.500 0.8424 0.01774 0.00905 -0.0102 0.1739 1.0000 6.750 0.8685 0.01837 0.00970 -0.0102 0.1684 1.0000 7.000 0.8948 0.01880 0.01020 -0.0101 0.1627 1.0000 7.250 0.9207 0.01939 0.01073 -0.0101 0.1581 1.0000 7.500 0.9466 0.02014 0.01155 -0.0101 0.1538 1.0000 7.750 0.9724 0.02065 0.01217 -0.0100 0.1490 1.0000 8.000 0.9981 0.02119 0.01269 -0.0099 0.1447 1.0000 8.250 1.0234 0.02213 0.01364 -0.0099 0.1407 1.0000 8.500 1.0485 0.02276 0.01447 -0.0097 0.1369 1.0000 8.750 1.0735 0.02340 0.01519 -0.0095 0.1331 1.0000 9.000 1.0985 0.02413 0.01587 -0.0095 0.1296 1.0000 9.250 1.1224 0.02521 0.01710 -0.0093 0.1261 1.0000 9.500 1.1458 0.02600 0.01810 -0.0090 0.1227 1.0000 9.750 1.1694 0.02679 0.01900 -0.0087 0.1195 1.0000 10.000 1.1934 0.02755 0.01977 -0.0086 0.1166 1.0000 10.250 1.2156 0.02906 0.02137 -0.0083 0.1136 1.0000 10.500 1.2360 0.03001 0.02261 -0.0077 0.1108 1.0000 10.750 1.2564 0.03110 0.02391 -0.0072 0.1080 1.0000 11.000 1.2777 0.03195 0.02487 -0.0067 0.1053 1.0000 11.250 1.3000 0.03293 0.02581 -0.0065 0.1027 1.0000 11.500 1.3162 0.03487 0.02799 -0.0058 0.1003 1.0000 11.750 1.3301 0.03638 0.02984 -0.0046 0.0981 1.0000 12.000 1.3442 0.03782 0.03154 -0.0036 0.0957 1.0000 12.250 1.3598 0.03877 0.03262 -0.0026 0.0932 1.0000 12.500 1.3806 0.03932 0.03310 -0.0023 0.0908 1.0000 12.750 1.3902 0.04164 0.03559 -0.0012 0.0885 1.0000 13.000 1.3912 0.04335 0.03766 0.0010 0.0866 1.0000 13.250 1.3927 0.04479 0.03934 0.0030 0.0843 1.0000 13.500 1.3964 0.04569 0.04037 0.0049 0.0821 1.0000 13.750 1.4180 0.04523 0.03975 0.0054 0.0794 1.0000 14.000 1.4200 0.04737 0.04196 0.0067 0.0773 1.0000 14.250 1.4066 0.04984 0.04475 0.0087 0.0761 1.0000 14.500 1.3935 0.05280 0.04798 0.0098 0.0746 1.0000 14.750 1.3816 0.05597 0.05137 0.0102 0.0731 1.0000 15.000 1.3799 0.05819 0.05371 0.0100 0.0712 1.0000 15.250 1.4113 0.05665 0.05193 0.0105 0.0682 1.0000 15.500 1.4003 0.06063 0.05604 0.0102 0.0670 1.0000 15.750 1.3754 0.06644 0.06215 0.0082 0.0665 1.0000 16.000 1.3437 0.07410 0.07009 0.0044 0.0662 1.0000 16.250 1.2999 0.08487 0.08112 -0.0019 0.0664 1.0000