XFOIL Version 6.96 Calculated polar for: NASA SC(2)-0710 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.000 -1.0358 0.09589 0.09331 -0.0376 1.0000 0.0104 -17.750 -1.0994 0.07908 0.07624 -0.0473 1.0000 0.0102 -17.500 -1.1354 0.06780 0.06475 -0.0544 1.0000 0.0102 -17.250 -1.1585 0.05960 0.05637 -0.0598 1.0000 0.0102 -17.000 -1.1749 0.05330 0.04992 -0.0637 1.0000 0.0102 -16.750 -1.1869 0.04836 0.04484 -0.0664 1.0000 0.0102 -16.500 -1.1951 0.04434 0.04070 -0.0681 1.0000 0.0103 -16.250 -1.2006 0.04098 0.03723 -0.0692 1.0000 0.0104 -16.000 -1.2035 0.03818 0.03432 -0.0696 1.0000 0.0104 -15.750 -1.2045 0.03582 0.03187 -0.0696 1.0000 0.0105 -15.500 -1.2046 0.03379 0.02976 -0.0690 1.0000 0.0106 -15.250 -1.2041 0.03202 0.02791 -0.0680 1.0000 0.0107 -15.000 -1.2044 0.03048 0.02629 -0.0663 1.0000 0.0108 -14.750 -1.2081 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0.3208 0.6455 -0.500 0.4575 0.00832 0.00213 -0.1210 0.2531 0.6521 -0.250 0.4847 0.00867 0.00228 -0.1209 0.1984 0.6588 0.000 0.5121 0.00897 0.00241 -0.1208 0.1554 0.6645 0.250 0.5395 0.00925 0.00257 -0.1207 0.1202 0.6690 0.500 0.5672 0.00950 0.00270 -0.1206 0.0960 0.6717 0.750 0.5952 0.00970 0.00283 -0.1206 0.0806 0.6739 1.000 0.6232 0.00990 0.00296 -0.1206 0.0688 0.6761 1.500 0.6790 0.01026 0.00326 -0.1204 0.0533 0.6806 1.750 0.7068 0.01046 0.00342 -0.1203 0.0468 0.6828 2.000 0.7345 0.01066 0.00359 -0.1202 0.0420 0.6849 2.250 0.7622 0.01085 0.00377 -0.1201 0.0385 0.6871 2.500 0.7899 0.01105 0.00395 -0.1200 0.0360 0.6896 2.750 0.8173 0.01127 0.00415 -0.1198 0.0334 0.6920 3.000 0.8449 0.01147 0.00435 -0.1197 0.0318 0.6941 3.250 0.8724 0.01167 0.00456 -0.1195 0.0302 0.6960 3.500 0.8996 0.01190 0.00478 -0.1193 0.0283 0.6980 3.750 0.9266 0.01215 0.00504 -0.1191 0.0264 0.7001 4.000 0.9538 0.01236 0.00527 -0.1188 0.0250 0.7022 4.250 0.9807 0.01261 0.00551 -0.1186 0.0230 0.7044 4.500 1.0074 0.01289 0.00578 -0.1183 0.0213 0.7066 4.750 1.0341 0.01315 0.00605 -0.1180 0.0197 0.7087 5.000 1.0605 0.01346 0.00634 -0.1176 0.0182 0.7107 5.250 1.0867 0.01376 0.00668 -0.1172 0.0173 0.7128 5.500 1.1129 0.01407 0.00702 -0.1168 0.0166 0.7150 5.750 1.1389 0.01440 0.00737 -0.1164 0.0158 0.7174 6.000 1.1646 0.01476 0.00774 -0.1159 0.0152 0.7199 6.250 1.1900 0.01516 0.00816 -0.1153 0.0146 0.7222 6.500 1.2152 0.01559 0.00862 -0.1148 0.0141 0.7243 6.750 1.2405 0.01597 0.00904 -0.1142 0.0139 0.7261 7.000 1.2655 0.01637 0.00950 -0.1136 0.0136 0.7280 7.250 1.2903 0.01679 0.00998 -0.1130 0.0134 0.7300 7.500 1.3148 0.01724 0.01048 -0.1123 0.0131 0.7320 7.750 1.3390 0.01770 0.01099 -0.1115 0.0129 0.7341 8.000 1.3630 0.01818 0.01152 -0.1108 0.0126 0.7363 8.250 1.3867 0.01867 0.01207 -0.1100 0.0124 0.7384 8.500 1.4102 0.01919 0.01262 -0.1092 0.0121 0.7404 8.750 1.4331 0.01975 0.01323 -0.1083 0.0118 0.7422 9.000 1.4553 0.02039 0.01393 -0.1072 0.0116 0.7441 9.250 1.4763 0.02114 0.01478 -0.1060 0.0113 0.7460 9.500 1.4966 0.02196 0.01568 -0.1047 0.0111 0.7481 9.750 1.5179 0.02259 0.01640 -0.1035 0.0111 0.7504 10.000 1.5386 0.02325 0.01715 -0.1023 0.0110 0.7527 10.250 1.5586 0.02396 0.01795 -0.1009 0.0109 0.7548 10.500 1.5780 0.02471 0.01880 -0.0995 0.0108 0.7569 10.750 1.5966 0.02549 0.01967 -0.0980 0.0107 0.7588 11.000 1.6142 0.02632 0.02061 -0.0963 0.0106 0.7609 11.250 1.6308 0.02719 0.02160 -0.0945 0.0105 0.7631 11.500 1.6463 0.02811 0.02263 -0.0925 0.0104 0.7653 11.750 1.6604 0.02909 0.02372 -0.0903 0.0103 0.7676 12.000 1.6730 0.03009 0.02484 -0.0879 0.0101 0.7699 12.250 1.6828 0.03116 0.02602 -0.0851 0.0101 0.7720 12.500 1.6892 0.03224 0.02722 -0.0817 0.0100 0.7739 12.750 1.6930 0.03338 0.02848 -0.0780 0.0099 0.7758 13.000 1.6968 0.03470 0.02992 -0.0746 0.0098 0.7777 13.250 1.7000 0.03611 0.03146 -0.0713 0.0098 0.7797 13.500 1.7014 0.03770 0.03319 -0.0680 0.0097 0.7818 13.750 1.7023 0.03941 0.03503 -0.0650 0.0096 0.7840 14.000 1.7014 0.04134 0.03708 -0.0620 0.0096 0.7862 14.250 1.7001 0.04339 0.03926 -0.0594 0.0095 0.7882 14.750 1.6913 0.04845 0.04459 -0.0549 0.0094 0.7917 15.000 1.6840 0.05153 0.04781 -0.0533 0.0093 0.7935 15.250 1.6735 0.05525 0.05169 -0.0523 0.0093 0.7952 15.500 1.6582 0.06002 0.05662 -0.0523 0.0092 0.7969 15.750 1.6384 0.06607 0.06286 -0.0538 0.0092 0.7985 16.000 1.6108 0.07464 0.07164 -0.0581 0.0092 0.7999 16.250 1.5592 0.09045 0.08777 -0.0689 0.0093 0.8004