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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.750 -0.5236 0.08750 0.08423 -0.0168 1.0000 0.0263 -8.500 -0.5274 0.08121 0.07789 -0.0244 1.0000 0.0264 -8.000 -0.5304 0.07100 0.06747 -0.0312 0.9941 0.0267 -7.750 -0.5185 0.06827 0.06480 -0.0315 0.9878 0.0272 -7.500 -0.5066 0.06503 0.06151 -0.0333 0.9817 0.0279 -7.250 -0.4948 0.06131 0.05767 -0.0354 0.9754 0.0286 -7.000 -0.4838 0.05745 0.05365 -0.0368 0.9685 0.0292 -6.750 -0.4714 0.05362 0.04962 -0.0376 0.9628 0.0295 -6.250 -0.4498 0.03909 0.03394 -0.0360 0.9501 0.0173 -6.000 -0.4317 0.03638 0.03099 -0.0355 0.9452 0.0171 -5.750 -0.4127 0.03359 0.02792 -0.0348 0.9408 0.0169 -5.500 -0.3928 0.03082 0.02480 -0.0338 0.9369 0.0167 -5.250 -0.3702 0.02809 0.02169 -0.0331 0.9324 0.0167 -5.000 -0.3468 0.02568 0.01888 -0.0323 0.9285 0.0168 -4.750 -0.3229 0.02366 0.01648 -0.0312 0.9250 0.0170 -4.500 -0.2972 0.02195 0.01437 -0.0305 0.9216 0.0174 -4.250 -0.2711 0.02094 0.01333 -0.0304 0.9176 0.0182 -4.000 -0.2453 0.02022 0.01253 -0.0301 0.9139 0.0194 -3.750 -0.2197 0.01923 0.01136 -0.0293 0.9106 0.0204 -3.500 -0.1937 0.01823 0.01020 -0.0286 0.9074 0.0210 -3.250 -0.1663 0.01736 0.00923 -0.0284 0.9032 0.0216 -3.000 -0.1416 0.01652 0.00844 -0.0277 0.8984 0.0225 -2.750 -0.1197 0.01592 0.00782 -0.0261 0.8925 0.0235 -2.500 -0.0953 0.01541 0.00727 -0.0251 0.8830 0.0258 -2.250 -0.0734 0.01479 0.00665 -0.0235 0.8751 0.0278 -2.000 -0.0487 0.01425 0.00611 -0.0226 0.8663 0.0297 -1.750 -0.0244 0.01382 0.00561 -0.0215 0.8588 0.0322 -1.500 0.0011 0.01336 0.00516 -0.0208 0.8497 0.0370 -1.250 0.0267 0.01296 0.00473 -0.0200 0.8408 0.0427 -1.000 0.0519 0.01254 0.00433 -0.0191 0.8312 0.0585 -0.750 0.0714 0.01009 0.00396 -0.0187 0.8202 0.5989 -0.500 0.0883 0.00954 0.00408 -0.0152 0.8081 0.7864 -0.250 0.1042 0.00946 0.00417 -0.0111 0.7952 0.8616 0.000 0.1212 0.00948 0.00419 -0.0074 0.7821 0.9048 0.250 0.1428 0.00947 0.00413 -0.0051 0.7665 0.9314 0.500 0.1705 0.00941 0.00396 -0.0046 0.7455 0.9416 0.750 0.1985 0.00933 0.00375 -0.0042 0.7165 0.9494 1.000 0.2262 0.00931 0.00350 -0.0037 0.6687 0.9576 1.250 0.2547 0.00954 0.00323 -0.0035 0.5746 0.9642 1.500 0.2839 0.01021 0.00321 -0.0041 0.4481 0.9712 1.750 0.3167 0.01077 0.00332 -0.0056 0.3737 0.9766 2.000 0.3498 0.01114 0.00343 -0.0071 0.3335 0.9827 2.250 0.3845 0.01143 0.00354 -0.0088 0.3060 0.9875 2.500 0.4189 0.01170 0.00366 -0.0106 0.2837 0.9928 2.750 0.4540 0.01197 0.00378 -0.0124 0.2649 0.9974 3.000 0.4831 0.01220 0.00391 -0.0130 0.2503 1.0000 3.250 0.5064 0.01241 0.00404 -0.0124 0.2388 1.0000 3.500 0.5302 0.01265 0.00419 -0.0119 0.2280 1.0000 3.750 0.5547 0.01290 0.00436 -0.0115 0.2175 1.0000 4.000 0.5802 0.01314 0.00455 -0.0113 0.2082 1.0000 4.250 0.6059 0.01343 0.00477 -0.0112 0.2003 1.0000 4.500 0.6322 0.01368 0.00500 -0.0111 0.1922 1.0000 4.750 0.6583 0.01400 0.00524 -0.0111 0.1847 1.0000 5.000 0.6850 0.01427 0.00551 -0.0111 0.1774 1.0000 5.250 0.7111 0.01463 0.00581 -0.0110 0.1712 1.0000 5.500 0.7379 0.01491 0.00611 -0.0111 0.1654 1.0000 5.750 0.7642 0.01525 0.00642 -0.0111 0.1594 1.0000 6.000 0.7904 0.01562 0.00678 -0.0111 0.1540 1.0000 6.250 0.8169 0.01594 0.00714 -0.0111 0.1486 1.0000 6.500 0.8428 0.01634 0.00751 -0.0110 0.1440 1.0000 6.750 0.8687 0.01675 0.00793 -0.0110 0.1397 1.0000 7.000 0.8948 0.01711 0.00835 -0.0109 0.1350 1.0000 7.250 0.9204 0.01752 0.00876 -0.0109 0.1306 1.0000 7.500 0.9455 0.01802 0.00925 -0.0108 0.1269 1.0000 7.750 0.9712 0.01844 0.00976 -0.0107 0.1234 1.0000 8.000 0.9965 0.01887 0.01026 -0.0106 0.1197 1.0000 8.250 1.0210 0.01937 0.01076 -0.0104 0.1161 1.0000 8.500 1.0454 0.01992 0.01135 -0.0102 0.1129 1.0000 8.750 1.0702 0.02041 0.01195 -0.0100 0.1097 1.0000 9.000 1.0944 0.02094 0.01256 -0.0098 0.1068 1.0000 9.250 1.1180 0.02150 0.01317 -0.0096 0.1039 1.0000 9.500 1.1405 0.02220 0.01387 -0.0092 0.1011 1.0000 9.750 1.1642 0.02276 0.01458 -0.0089 0.0984 1.0000 10.000 1.1872 0.02338 0.01533 -0.0086 0.0957 1.0000 10.250 1.2095 0.02402 0.01606 -0.0082 0.0932 1.0000 10.500 1.2307 0.02471 0.01680 -0.0077 0.0909 1.0000 10.750 1.2511 0.02554 0.01768 -0.0072 0.0886 1.0000 11.000 1.2722 0.02626 0.01861 -0.0067 0.0862 1.0000 11.250 1.2922 0.02705 0.01954 -0.0061 0.0840 1.0000 11.500 1.3113 0.02782 0.02044 -0.0054 0.0818 1.0000 11.750 1.3292 0.02862 0.02132 -0.0046 0.0798 1.0000 12.000 1.3449 0.02965 0.02237 -0.0037 0.0778 1.0000 12.250 1.3612 0.03059 0.02354 -0.0028 0.0760 1.0000 12.500 1.3746 0.03156 0.02470 -0.0015 0.0739 1.0000 12.750 1.3866 0.03250 0.02580 -0.0002 0.0717 1.0000 13.000 1.3974 0.03347 0.02687 0.0010 0.0696 1.0000 13.250 1.4059 0.03465 0.02809 0.0023 0.0676 1.0000 13.500 1.4148 0.03599 0.02964 0.0034 0.0656 1.0000 13.750 1.4231 0.03739 0.03125 0.0044 0.0633 1.0000 14.000 1.4302 0.03885 0.03287 0.0052 0.0611 1.0000 14.250 1.4355 0.04047 0.03457 0.0059 0.0589 1.0000 14.500 1.4380 0.04250 0.03671 0.0064 0.0570 1.0000 14.750 1.4412 0.04470 0.03915 0.0067 0.0548 1.0000 15.000 1.4421 0.04719 0.04183 0.0067 0.0527 1.0000 15.250 1.4402 0.05012 0.04492 0.0064 0.0511 1.0000 15.500 1.4347 0.05367 0.04860 0.0055 0.0498 1.0000 15.750 1.4254 0.05802 0.05308 0.0039 0.0488 1.0000 16.000 1.4138 0.06315 0.05845 0.0016 0.0478 1.0000 16.250 1.3967 0.06958 0.06513 -0.0018 0.0470 1.0000 16.500 1.3729 0.07776 0.07353 -0.0066 0.0465 1.0000 16.750 1.3407 0.08790 0.08389 -0.0127 0.0464 1.0000 17.000 1.2998 0.09981 0.09597 -0.0195 0.0467 1.0000 17.250 1.2501 0.11347 0.10979 -0.0271 0.0472 1.0000 17.500 1.1898 0.12978 0.12624 -0.0362 0.0478 1.0000