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 = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.750 -0.4674 0.08132 0.07982 0.0003 0.9194 0.0115 -8.500 -0.4736 0.07625 0.07476 -0.0018 0.9165 0.0116 -8.250 -0.6114 0.07367 0.07203 -0.0077 0.9200 0.0111 -8.000 -0.6117 0.06920 0.06748 -0.0098 0.9157 0.0112 -7.750 -0.6085 0.06527 0.06347 -0.0111 0.9121 0.0113 -7.500 -0.6023 0.06166 0.05976 -0.0119 0.9088 0.0114 -7.250 -0.5919 0.05813 0.05613 -0.0129 0.9056 0.0115 -7.000 -0.5799 0.05464 0.05253 -0.0136 0.9021 0.0117 -6.750 -0.5665 0.05115 0.04892 -0.0140 0.8988 0.0119 -6.500 -0.5517 0.04757 0.04518 -0.0141 0.8959 0.0124 -6.250 -0.5311 0.04048 0.03761 -0.0129 0.8929 0.0139 -6.000 -0.5206 0.03381 0.03056 -0.0126 0.8897 0.0142 -5.750 -0.4994 0.03190 0.02856 -0.0126 0.8867 0.0144 -5.500 -0.4772 0.03016 0.02670 -0.0125 0.8838 0.0146 -5.250 -0.4542 0.02839 0.02479 -0.0122 0.8811 0.0149 -5.000 -0.4306 0.02650 0.02272 -0.0118 0.8784 0.0154 -4.750 -0.4051 0.02431 0.02030 -0.0115 0.8755 0.0162 -4.500 -0.3791 0.02082 0.01619 -0.0103 0.8715 0.0178 -4.250 -0.3536 0.01646 0.01148 -0.0091 0.8667 0.0132 -4.000 -0.3285 0.01315 0.00773 -0.0078 0.8618 0.0120 -3.750 -0.3004 0.01225 0.00675 -0.0076 0.8564 0.0123 -3.500 -0.2729 0.01154 0.00596 -0.0074 0.8510 0.0127 -3.250 -0.2456 0.01101 0.00534 -0.0070 0.8461 0.0133 -3.000 -0.2168 0.01057 0.00487 -0.0071 0.8406 0.0138 -2.750 -0.1892 0.00984 0.00408 -0.0070 0.8346 0.0144 -2.500 -0.1612 0.00948 0.00370 -0.0069 0.8289 0.0151 -2.250 -0.1319 0.00918 0.00340 -0.0071 0.8224 0.0161 -2.000 -0.1034 0.00895 0.00313 -0.0071 0.8155 0.0171 -1.750 -0.0741 0.00859 0.00276 -0.0073 0.8084 0.0188 -1.500 -0.0451 0.00839 0.00255 -0.0074 0.7999 0.0205 -1.250 -0.0156 0.00814 0.00227 -0.0076 0.7903 0.0224 -1.000 0.0136 0.00795 0.00206 -0.0078 0.7816 0.0252 -0.750 0.0433 0.00776 0.00186 -0.0081 0.7700 0.0295 -0.500 0.0729 0.00759 0.00168 -0.0083 0.7553 0.0379 -0.250 0.1025 0.00588 0.00138 -0.0099 0.7374 0.4979 0.000 0.1319 0.00514 0.00134 -0.0105 0.7084 0.7307 0.250 0.1613 0.00514 0.00134 -0.0107 0.6597 0.7890 0.500 0.1908 0.00543 0.00141 -0.0111 0.5678 0.8352 0.750 0.2198 0.00603 0.00157 -0.0116 0.4350 0.8658 1.000 0.2471 0.00642 0.00172 -0.0116 0.3620 0.8882 1.250 0.2746 0.00665 0.00182 -0.0114 0.3264 0.9027 1.500 0.3026 0.00684 0.00189 -0.0115 0.2998 0.9127 1.750 0.3304 0.00701 0.00196 -0.0114 0.2778 0.9194 2.000 0.3582 0.00716 0.00203 -0.0114 0.2602 0.9266 2.250 0.3858 0.00730 0.00209 -0.0113 0.2455 0.9333 2.500 0.4126 0.00744 0.00217 -0.0110 0.2320 0.9401 2.750 0.4399 0.00757 0.00224 -0.0109 0.2201 0.9469 3.000 0.4654 0.00768 0.00231 -0.0103 0.2095 0.9538 3.250 0.4918 0.00782 0.00239 -0.0100 0.1996 0.9608 3.500 0.5164 0.00790 0.00244 -0.0092 0.1915 0.9684 3.750 0.5423 0.00800 0.00251 -0.0087 0.1836 0.9759 4.000 0.5695 0.00811 0.00257 -0.0086 0.1758 0.9840 4.250 0.6013 0.00825 0.00267 -0.0096 0.1681 0.9893 4.500 0.6339 0.00840 0.00278 -0.0107 0.1611 0.9948 4.750 0.6669 0.00857 0.00291 -0.0120 0.1545 1.0000 5.000 0.6958 0.00874 0.00305 -0.0124 0.1489 1.0000 5.250 0.7246 0.00897 0.00322 -0.0129 0.1417 1.0000 5.500 0.7539 0.00911 0.00336 -0.0134 0.1380 1.0000 5.750 0.7829 0.00931 0.00353 -0.0138 0.1329 1.0000 6.000 0.8117 0.00956 0.00375 -0.0143 0.1275 1.0000 6.250 0.8407 0.00972 0.00391 -0.0147 0.1242 1.0000 6.500 0.8694 0.00994 0.00410 -0.0151 0.1197 1.0000 6.750 0.8977 0.01024 0.00437 -0.0155 0.1143 1.0000 7.000 0.9264 0.01041 0.00456 -0.0158 0.1122 1.0000 7.250 0.9547 0.01062 0.00478 -0.0162 0.1091 1.0000 7.500 0.9827 0.01089 0.00502 -0.0165 0.1053 1.0000 7.750 1.0102 0.01122 0.00535 -0.0167 0.1011 1.0000 8.000 1.0383 0.01141 0.00557 -0.0170 0.0992 1.0000 8.250 1.0660 0.01165 0.00582 -0.0172 0.0966 1.0000 8.500 1.0933 0.01194 0.00610 -0.0174 0.0936 1.0000 8.750 1.1196 0.01238 0.00654 -0.0175 0.0892 1.0000 9.000 1.1472 0.01258 0.00677 -0.0177 0.0878 1.0000 9.250 1.1744 0.01281 0.00704 -0.0179 0.0856 1.0000 9.500 1.2011 0.01311 0.00733 -0.0180 0.0827 1.0000 9.750 1.2268 0.01354 0.00775 -0.0181 0.0789 1.0000 10.000 1.2531 0.01384 0.00809 -0.0181 0.0768 1.0000 10.250 1.2796 0.01411 0.00840 -0.0182 0.0750 1.0000 10.500 1.3055 0.01443 0.00876 -0.0182 0.0727 1.0000 10.750 1.3306 0.01483 0.00915 -0.0182 0.0698 1.0000 11.000 1.3552 0.01530 0.00963 -0.0181 0.0668 1.0000 11.250 1.3809 0.01557 0.00996 -0.0181 0.0652 1.0000 11.500 1.4058 0.01593 0.01035 -0.0180 0.0629 1.0000 11.750 1.4298 0.01637 0.01080 -0.0178 0.0603 1.0000 12.000 1.4526 0.01693 0.01139 -0.0175 0.0574 1.0000 12.250 1.4771 0.01725 0.01177 -0.0174 0.0559 1.0000 12.500 1.5006 0.01767 0.01223 -0.0171 0.0535 1.0000 12.750 1.5226 0.01823 0.01278 -0.0168 0.0506 1.0000 13.000 1.5443 0.01876 0.01337 -0.0163 0.0482 1.0000 13.250 1.5664 0.01923 0.01389 -0.0159 0.0460 1.0000 13.500 1.5863 0.01988 0.01453 -0.0153 0.0429 1.0000 13.750 1.6058 0.02052 0.01523 -0.0147 0.0402 1.0000 14.000 1.6241 0.02121 0.01595 -0.0139 0.0369 1.0000 14.250 1.6395 0.02207 0.01683 -0.0128 0.0331 1.0000 14.500 1.6488 0.02318 0.01793 -0.0110 0.0282 1.0000 14.750 1.6551 0.02455 0.01931 -0.0091 0.0225 1.0000 15.000 1.6561 0.02638 0.02115 -0.0069 0.0164 1.0000 15.250 1.6549 0.02845 0.02326 -0.0048 0.0125 1.0000 15.500 1.6560 0.03038 0.02529 -0.0031 0.0106 1.0000 15.750 1.6553 0.03256 0.02756 -0.0017 0.0096 1.0000 16.000 1.6559 0.03472 0.02984 -0.0006 0.0090 1.0000 16.250 1.6552 0.03710 0.03233 0.0003 0.0086 1.0000 16.500 1.6514 0.03994 0.03529 0.0008 0.0082 1.0000 16.750 1.6440 0.04335 0.03883 0.0008 0.0079 1.0000 17.000 1.6330 0.04749 0.04311 0.0002 0.0077 1.0000 17.250 1.6171 0.05267 0.04846 -0.0013 0.0075 1.0000 17.500 1.5964 0.05925 0.05522 -0.0043 0.0075 1.0000 17.750 1.5684 0.06792 0.06410 -0.0091 0.0075 1.0000 18.000 1.5287 0.07971 0.07615 -0.0160 0.0077 1.0000 18.250 1.4747 0.09370 0.09039 -0.0232 0.0082 1.0000 18.500 1.4083 0.10942 0.10635 -0.0310 0.0088 1.0000