XFOIL Version 6.96 Calculated polar for: NASA SC(2)-0614 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.500 -1.0164 0.09911 0.09546 -0.0473 1.0000 0.0313 -18.250 -1.0554 0.08801 0.08409 -0.0541 1.0000 0.0312 -18.000 -1.0795 0.08010 0.07598 -0.0588 1.0000 0.0313 -17.750 -1.0969 0.07374 0.06943 -0.0623 1.0000 0.0315 -17.500 -1.1101 0.06833 0.06385 -0.0650 1.0000 0.0316 -17.250 -1.1198 0.06370 0.05905 -0.0672 1.0000 0.0318 -17.000 -1.1269 0.05964 0.05483 -0.0689 1.0000 0.0320 -16.750 -1.1315 0.05606 0.05109 -0.0702 1.0000 0.0322 -16.500 -1.1343 0.05288 0.04776 -0.0711 1.0000 0.0323 -16.250 -1.1354 0.05007 0.04480 -0.0718 1.0000 0.0325 -16.000 -1.1360 0.04727 0.04190 -0.0717 1.0000 0.0329 -15.750 -1.1316 0.04517 0.03974 -0.0716 1.0000 0.0332 -15.500 -1.1255 0.04331 0.03784 -0.0715 1.0000 0.0336 -15.250 -1.1186 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0.00627 -0.0900 0.9680 0.1157 -5.750 -0.2749 0.01193 0.00589 -0.0933 0.9675 0.1371 -5.500 -0.2425 0.01144 0.00558 -0.0950 0.9636 0.1695 -5.250 -0.2028 0.01077 0.00519 -0.0985 0.9620 0.2296 -5.000 -0.1588 0.00985 0.00471 -0.1032 0.9612 0.3253 -4.750 -0.1098 0.00873 0.00425 -0.1093 0.9613 0.4762 -4.500 -0.0718 0.00851 0.00425 -0.1116 0.9594 0.5446 -4.250 -0.0361 0.00848 0.00426 -0.1131 0.9574 0.5710 -4.000 -0.0008 0.00847 0.00425 -0.1145 0.9555 0.5876 -3.750 0.0345 0.00847 0.00424 -0.1159 0.9539 0.5996 -3.500 0.0648 0.00853 0.00430 -0.1162 0.9498 0.6086 -3.250 0.0953 0.00856 0.00433 -0.1166 0.9454 0.6163 -3.000 0.1270 0.00861 0.00440 -0.1170 0.9420 0.6245 -2.750 0.1598 0.00863 0.00440 -0.1177 0.9388 0.6321 -2.500 0.1866 0.00872 0.00453 -0.1170 0.9319 0.6382 -2.250 0.2174 0.00870 0.00446 -0.1172 0.9255 0.6445 -2.000 0.2449 0.00872 0.00451 -0.1165 0.9180 0.6493 -1.750 0.2715 0.00878 0.00459 -0.1155 0.9088 0.6548 -1.500 0.3007 0.00884 0.00460 -0.1154 0.8991 0.6615 -1.250 0.3266 0.00887 0.00465 -0.1142 0.8885 0.6654 -1.000 0.3529 0.00892 0.00471 -0.1132 0.8748 0.6689 -0.750 0.3812 0.00893 0.00469 -0.1129 0.8613 0.6721 -0.500 0.4111 0.00894 0.00466 -0.1130 0.8488 0.6761 -0.250 0.4401 0.00893 0.00460 -0.1129 0.8347 0.6788 0.000 0.4682 0.00895 0.00459 -0.1125 0.8197 0.6805 0.250 0.4967 0.00896 0.00460 -0.1124 0.8033 0.6820 0.500 0.5249 0.00902 0.00461 -0.1121 0.7826 0.6839 0.750 0.5528 0.00910 0.00462 -0.1117 0.7543 0.6861 1.000 0.5803 0.00925 0.00461 -0.1114 0.7111 0.6882 1.250 0.6040 0.00973 0.00463 -0.1103 0.6100 0.6903 1.500 0.6233 0.01078 0.00492 -0.1088 0.4596 0.6923 1.750 0.6459 0.01158 0.00521 -0.1081 0.3540 0.6939 2.000 0.6688 0.01227 0.00549 -0.1073 0.2658 0.6953 2.250 0.6932 0.01282 0.00576 -0.1067 0.2084 0.6966 2.500 0.7184 0.01330 0.00603 -0.1062 0.1653 0.6982 2.750 0.7442 0.01372 0.00630 -0.1058 0.1375 0.7000 3.000 0.7703 0.01413 0.00658 -0.1054 0.1166 0.7019 3.500 0.8244 0.01480 0.00709 -0.1051 0.0944 0.7058 3.750 0.8517 0.01512 0.00737 -0.1050 0.0878 0.7077 4.000 0.8789 0.01546 0.00765 -0.1049 0.0827 0.7095 4.250 0.9045 0.01580 0.00800 -0.1044 0.0786 0.7110 4.500 0.9306 0.01607 0.00829 -0.1040 0.0753 0.7125 4.750 0.9554 0.01650 0.00869 -0.1033 0.0720 0.7140 5.000 0.9806 0.01689 0.00911 -0.1027 0.0696 0.7157 5.250 1.0066 0.01720 0.00944 -0.1023 0.0672 0.7175 5.500 1.0322 0.01755 0.00978 -0.1019 0.0647 0.7195 5.750 1.0559 0.01813 0.01034 -0.1011 0.0622 0.7217 6.000 1.0825 0.01840 0.01065 -0.1008 0.0601 0.7238 6.250 1.1082 0.01874 0.01098 -0.1004 0.0580 0.7258 6.500 1.1311 0.01924 0.01147 -0.0995 0.0559 0.7275 6.750 1.1536 0.01978 0.01207 -0.0985 0.0541 0.7295 7.000 1.1774 0.02018 0.01252 -0.0976 0.0523 0.7317 7.250 1.2007 0.02062 0.01298 -0.0967 0.0506 0.7341 7.500 1.2215 0.02137 0.01370 -0.0956 0.0489 0.7364 7.750 1.2445 0.02190 0.01429 -0.0947 0.0474 0.7388 8.000 1.2679 0.02236 0.01479 -0.0939 0.0459 0.7411 8.250 1.2900 0.02282 0.01528 -0.0929 0.0446 0.7430 8.500 1.3100 0.02344 0.01592 -0.0916 0.0435 0.7449 8.750 1.3277 0.02444 0.01694 -0.0899 0.0424 0.7468 9.000 1.3482 0.02496 0.01757 -0.0886 0.0415 0.7490 9.250 1.3676 0.02558 0.01827 -0.0871 0.0406 0.7516 9.500 1.3863 0.02622 0.01896 -0.0856 0.0397 0.7544 9.750 1.4042 0.02688 0.01965 -0.0840 0.0389 0.7571 10.000 1.4191 0.02757 0.02036 -0.0819 0.0383 0.7593 10.250 1.4310 0.02854 0.02136 -0.0794 0.0376 0.7613 10.500 1.4447 0.02961 0.02253 -0.0772 0.0370 0.7634 10.750 1.4592 0.03036 0.02340 -0.0751 0.0364 0.7658 11.000 1.4733 0.03122 0.02437 -0.0731 0.0358 0.7683 11.250 1.4868 0.03216 0.02541 -0.0712 0.0352 0.7710 11.500 1.4999 0.03317 0.02649 -0.0692 0.0347 0.7736 11.750 1.5122 0.03418 0.02757 -0.0673 0.0342 0.7760 12.000 1.5232 0.03523 0.02870 -0.0652 0.0338 0.7783 12.250 1.5334 0.03638 0.02992 -0.0632 0.0334 0.7807 12.500 1.5425 0.03775 0.03134 -0.0611 0.0330 0.7833 12.750 1.5493 0.03966 0.03333 -0.0590 0.0326 0.7858 13.000 1.5551 0.04142 0.03524 -0.0569 0.0323 0.7884 13.250 1.5606 0.04310 0.03706 -0.0549 0.0320 0.7910 13.500 1.5644 0.04495 0.03907 -0.0530 0.0318 0.7932 13.750 1.5666 0.04695 0.04124 -0.0510 0.0315 0.7953 14.000 1.5675 0.04914 0.04360 -0.0492 0.0312 0.7975 14.250 1.5674 0.05150 0.04612 -0.0477 0.0309 0.7998 14.500 1.5659 0.05405 0.04881 -0.0463 0.0306 0.8023 14.750 1.5633 0.05684 0.05174 -0.0453 0.0303 0.8048 15.000 1.5604 0.05977 0.05481 -0.0446 0.0301 0.8072 15.250 1.5557 0.06300 0.05817 -0.0441 0.0298 0.8093 15.500 1.5496 0.06651 0.06182 -0.0440 0.0296 0.8112 15.750 1.5423 0.07038 0.06584 -0.0442 0.0294 0.8132 16.000 1.5335 0.07470 0.07031 -0.0450 0.0293 0.8153 16.250 1.5232 0.07949 0.07524 -0.0463 0.0292 0.8174 16.500 1.5113 0.08483 0.08073 -0.0483 0.0290 0.8195 16.750 1.4961 0.09105 0.08711 -0.0511 0.0289 0.8215 17.000 1.4784 0.09808 0.09431 -0.0548 0.0288 0.8233 17.250 1.4550 0.10657 0.10300 -0.0598 0.0288 0.8246 17.500 1.4193 0.11819 0.11490 -0.0675 0.0288 0.8254