XFOIL Version 6.96 Calculated polar for: NASA SC(2)-0414 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 ------ -------- --------- --------- -------- -------- -------- -19.750 -1.2655 0.09714 0.09353 -0.0314 1.0000 0.0229 -19.500 -1.2842 0.09055 0.08682 -0.0346 1.0000 0.0231 -19.250 -1.2994 0.08455 0.08071 -0.0376 1.0000 0.0233 -19.000 -1.3118 0.07906 0.07513 -0.0402 1.0000 0.0234 -18.750 -1.3219 0.07404 0.07001 -0.0425 1.0000 0.0236 -18.500 -1.3289 0.06955 0.06544 -0.0445 1.0000 0.0238 -18.250 -1.3334 0.06550 0.06130 -0.0462 1.0000 0.0240 -18.000 -1.3359 0.06186 0.05758 -0.0476 1.0000 0.0242 -17.750 -1.3363 0.05857 0.05422 -0.0488 1.0000 0.0244 -17.500 -1.3351 0.05555 0.05113 -0.0498 1.0000 0.0246 -17.250 -1.3329 0.05275 0.04826 -0.0506 1.0000 0.0248 -17.000 -1.3299 0.05014 0.04556 -0.0513 1.0000 0.0251 -16.750 -1.3261 0.04766 0.04301 -0.0518 1.0000 0.0253 -16.500 -1.3208 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-0.0873 0.1863 0.6762 2.500 0.5847 0.01005 0.00360 -0.0873 0.1571 0.6778 2.750 0.6131 0.01030 0.00374 -0.0874 0.1359 0.6793 3.000 0.6416 0.01055 0.00389 -0.0874 0.1198 0.6806 3.250 0.6702 0.01076 0.00404 -0.0875 0.1082 0.6819 3.500 0.6985 0.01095 0.00418 -0.0876 0.0983 0.6840 3.750 0.7268 0.01116 0.00435 -0.0876 0.0913 0.6858 4.000 0.7550 0.01135 0.00453 -0.0876 0.0856 0.6874 4.250 0.7830 0.01159 0.00473 -0.0875 0.0805 0.6890 4.500 0.8112 0.01180 0.00493 -0.0875 0.0762 0.6907 4.750 0.8392 0.01201 0.00513 -0.0874 0.0720 0.6925 5.000 0.8670 0.01226 0.00535 -0.0873 0.0680 0.6943 5.250 0.8950 0.01247 0.00555 -0.0872 0.0648 0.6962 5.500 0.9222 0.01278 0.00581 -0.0870 0.0611 0.6979 5.750 0.9502 0.01298 0.00602 -0.0870 0.0590 0.6994 6.000 0.9776 0.01322 0.00624 -0.0868 0.0564 0.7010 6.250 1.0045 0.01351 0.00653 -0.0866 0.0537 0.7033 6.500 1.0319 0.01372 0.00676 -0.0864 0.0519 0.7051 6.750 1.0587 0.01399 0.00703 -0.0862 0.0499 0.7069 7.000 1.0844 0.01440 0.00743 -0.0857 0.0477 0.7086 7.250 1.1114 0.01463 0.00769 -0.0855 0.0464 0.7104 7.500 1.1379 0.01491 0.00799 -0.0852 0.0449 0.7124 7.750 1.1636 0.01527 0.00833 -0.0848 0.0432 0.7145 8.000 1.1888 0.01569 0.00876 -0.0842 0.0417 0.7163 8.250 1.2150 0.01597 0.00906 -0.0839 0.0406 0.7178 8.500 1.2407 0.01630 0.00940 -0.0834 0.0394 0.7191 8.750 1.2657 0.01666 0.00977 -0.0829 0.0382 0.7215 9.000 1.2886 0.01724 0.01036 -0.0821 0.0368 0.7236 9.250 1.3137 0.01754 0.01072 -0.0815 0.0362 0.7255 9.500 1.3382 0.01790 0.01111 -0.0809 0.0354 0.7274 9.750 1.3624 0.01827 0.01152 -0.0802 0.0345 0.7293 10.000 1.3859 0.01868 0.01194 -0.0795 0.0337 0.7313 10.250 1.4075 0.01927 0.01253 -0.0785 0.0327 0.7333 10.500 1.4287 0.01986 0.01317 -0.0773 0.0320 0.7352 10.750 1.4514 0.02028 0.01364 -0.0765 0.0315 0.7370 11.000 1.4733 0.02074 0.01414 -0.0755 0.0310 0.7389 11.250 1.4946 0.02120 0.01466 -0.0744 0.0304 0.7415 11.500 1.5151 0.02170 0.01520 -0.0732 0.0299 0.7437 11.750 1.5344 0.02225 0.01579 -0.0718 0.0294 0.7458 12.000 1.5516 0.02290 0.01648 -0.0701 0.0288 0.7479 12.250 1.5641 0.02379 0.01741 -0.0678 0.0283 0.7501 12.500 1.5738 0.02463 0.01832 -0.0649 0.0279 0.7523 12.750 1.5870 0.02525 0.01901 -0.0625 0.0276 0.7543 13.000 1.6010 0.02595 0.01978 -0.0605 0.0273 0.7561 13.250 1.6145 0.02670 0.02060 -0.0585 0.0270 0.7588 13.500 1.6275 0.02749 0.02148 -0.0565 0.0267 0.7612 13.750 1.6398 0.02835 0.02241 -0.0546 0.0263 0.7636 14.000 1.6518 0.02926 0.02338 -0.0527 0.0259 0.7660 14.250 1.6625 0.03029 0.02447 -0.0508 0.0256 0.7684 14.500 1.6719 0.03144 0.02569 -0.0489 0.0253 0.7708 14.750 1.6798 0.03276 0.02706 -0.0470 0.0251 0.7729 15.000 1.6847 0.03434 0.02872 -0.0450 0.0248 0.7758 15.250 1.6855 0.03635 0.03082 -0.0430 0.0245 0.7784 15.500 1.6806 0.03894 0.03354 -0.0408 0.0241 0.7810 15.750 1.6849 0.04083 0.03554 -0.0395 0.0240 0.7837 16.000 1.6899 0.04274 0.03755 -0.0384 0.0239 0.7864 16.250 1.6929 0.04491 0.03982 -0.0375 0.0237 0.7888 16.500 1.6946 0.04729 0.04231 -0.0367 0.0236 0.7912 16.750 1.6946 0.04995 0.04509 -0.0361 0.0234 0.7939 17.000 1.6928 0.05291 0.04818 -0.0358 0.0233 0.7964 17.250 1.6891 0.05621 0.05160 -0.0358 0.0231 0.7989 17.500 1.6835 0.05994 0.05546 -0.0361 0.0230 0.8013 17.750 1.6764 0.06410 0.05974 -0.0370 0.0228 0.8037 18.000 1.6670 0.06880 0.06456 -0.0383 0.0227 0.8058 18.250 1.6554 0.07408 0.06998 -0.0401 0.0226 0.8078 18.500 1.6403 0.08019 0.07625 -0.0427 0.0225 0.8101 18.750 1.6230 0.08696 0.08317 -0.0459 0.0224 0.8121 19.000 1.6016 0.09459 0.09096 -0.0498 0.0223 0.8138 19.250 1.5761 0.10317 0.09971 -0.0544 0.0223 0.8154