XFOIL Version 6.96 Calculated polar for: NASA LRN 1015 (NASA TM 102840) 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 ------ -------- --------- --------- -------- -------- -------- -11.750 -0.1002 0.09492 0.09189 -0.1057 0.7488 0.0127 -11.500 -0.0944 0.09198 0.08893 -0.1071 0.7472 0.0128 -11.250 -0.0884 0.08910 0.08605 -0.1085 0.7456 0.0128 -11.000 -0.0825 0.08646 0.08343 -0.1095 0.7447 0.0130 -10.750 -0.0792 0.08324 0.08024 -0.1109 0.7436 0.0131 -10.500 -0.0754 0.08022 0.07724 -0.1123 0.7422 0.0132 -10.250 -0.0730 0.07695 0.07399 -0.1138 0.7409 0.0134 -10.000 -0.0708 0.07369 0.07074 -0.1154 0.7395 0.0137 -9.750 -0.0726 0.06968 0.06675 -0.1175 0.7381 0.0138 -9.500 -0.0776 0.06509 0.06219 -0.1201 0.7366 0.0140 -9.250 -0.0987 0.05725 0.05438 -0.1268 0.7348 0.0139 -9.000 -0.1222 0.05220 0.04927 -0.1290 0.7328 0.0139 -8.750 -0.1430 0.04930 0.04629 -0.1270 0.7304 0.0141 -8.500 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0.00252 -0.1016 0.6622 0.8321 1.250 0.7008 0.00655 0.00249 -0.1016 0.6588 0.8363 1.500 0.7288 0.00656 0.00247 -0.1016 0.6554 0.8404 1.750 0.7569 0.00660 0.00249 -0.1017 0.6518 0.8446 2.000 0.7847 0.00660 0.00251 -0.1018 0.6478 0.8483 2.250 0.8124 0.00658 0.00250 -0.1018 0.6437 0.8519 2.500 0.8399 0.00660 0.00250 -0.1018 0.6397 0.8552 2.750 0.8675 0.00662 0.00254 -0.1018 0.6356 0.8586 3.000 0.8951 0.00664 0.00258 -0.1018 0.6309 0.8620 3.250 0.9225 0.00667 0.00259 -0.1018 0.6255 0.8649 3.500 0.9494 0.00669 0.00263 -0.1018 0.6199 0.8682 3.750 0.9764 0.00671 0.00267 -0.1017 0.6136 0.8713 4.000 1.0026 0.00677 0.00272 -0.1015 0.6071 0.8747 4.250 1.0293 0.00682 0.00279 -0.1014 0.5988 0.8782 4.500 1.0551 0.00690 0.00285 -0.1011 0.5902 0.8814 4.750 1.0792 0.00699 0.00293 -0.1005 0.5777 0.8851 5.000 1.1024 0.00712 0.00303 -0.0997 0.5609 0.8888 5.250 1.1230 0.00736 0.00319 -0.0985 0.5365 0.8930 5.500 1.1410 0.00769 0.00341 -0.0968 0.5086 0.8973 5.750 1.1551 0.00809 0.00371 -0.0944 0.4773 0.9026 6.000 1.1647 0.00864 0.00409 -0.0911 0.4416 0.9092 6.250 1.1731 0.00914 0.00448 -0.0877 0.4105 0.9168 6.500 1.1772 0.00960 0.00485 -0.0834 0.3837 0.9283 6.750 1.1803 0.01010 0.00532 -0.0790 0.3587 0.9533 7.000 1.1988 0.01084 0.00594 -0.0784 0.3289 1.0000 7.250 1.2055 0.01150 0.00651 -0.0753 0.3089 1.0000 7.500 1.2097 0.01233 0.00726 -0.0721 0.2889 1.0000 7.750 1.2158 0.01327 0.00812 -0.0695 0.2728 1.0000 8.000 1.2237 0.01422 0.00902 -0.0673 0.2574 1.0000 8.250 1.2326 0.01517 0.00990 -0.0654 0.2430 1.0000 8.500 1.2421 0.01611 0.01079 -0.0635 0.2296 1.0000 8.750 1.2518 0.01705 0.01168 -0.0617 0.2171 1.0000 9.000 1.2614 0.01801 0.01258 -0.0600 0.2049 1.0000 9.250 1.2726 0.01891 0.01345 -0.0584 0.1939 1.0000 9.500 1.2839 0.01981 0.01431 -0.0569 0.1835 1.0000 9.750 1.2941 0.02079 0.01525 -0.0554 0.1740 1.0000 10.000 1.3057 0.02170 0.01613 -0.0540 0.1648 1.0000 10.250 1.3173 0.02262 0.01704 -0.0527 0.1569 1.0000 10.500 1.3279 0.02362 0.01800 -0.0513 0.1487 1.0000 10.750 1.3407 0.02450 0.01888 -0.0502 0.1421 1.0000 11.000 1.3506 0.02557 0.01992 -0.0489 0.1348 1.0000 11.250 1.3632 0.02649 0.02085 -0.0478 0.1287 1.0000 11.500 1.3741 0.02753 0.02188 -0.0466 0.1226 1.0000 11.750 1.3854 0.02859 0.02294 -0.0455 0.1169 1.0000 12.000 1.3972 0.02964 0.02398 -0.0445 0.1116 1.0000 12.250 1.4071 0.03085 0.02518 -0.0434 0.1057 1.0000 12.500 1.4195 0.03191 0.02626 -0.0426 0.1012 1.0000 12.750 1.4296 0.03313 0.02747 -0.0416 0.0967 1.0000 13.000 1.4407 0.03432 0.02867 -0.0408 0.0912 1.0000 13.250 1.4510 0.03559 0.02993 -0.0399 0.0870 1.0000 13.500 1.4609 0.03691 0.03126 -0.0390 0.0836 1.0000 13.750 1.4722 0.03814 0.03253 -0.0383 0.0804 1.0000 14.000 1.4833 0.03939 0.03381 -0.0376 0.0780 1.0000 14.250 1.4929 0.04078 0.03520 -0.0369 0.0748 1.0000 14.500 1.5002 0.04240 0.03684 -0.0361 0.0715 1.0000 14.750 1.5118 0.04368 0.03817 -0.0356 0.0700 1.0000 15.000 1.5229 0.04500 0.03954 -0.0350 0.0684 1.0000 15.250 1.5317 0.04656 0.04113 -0.0345 0.0662 1.0000 15.500 1.5399 0.04817 0.04276 -0.0339 0.0644 1.0000 15.750 1.5459 0.05002 0.04464 -0.0333 0.0619 1.0000 16.000 1.5542 0.05168 0.04638 -0.0328 0.0605 1.0000 16.250 1.5649 0.05313 0.04789 -0.0325 0.0592 1.0000 16.500 1.5730 0.05485 0.04966 -0.0322 0.0573 1.0000 16.750 1.5791 0.05679 0.05160 -0.0318 0.0546 1.0000 17.000 1.5826 0.05902 0.05387 -0.0314 0.0522 1.0000 17.250 1.5912 0.06076 0.05568 -0.0312 0.0508 1.0000 17.500 1.5981 0.06268 0.05766 -0.0311 0.0491 1.0000 17.750 1.6020 0.06498 0.05999 -0.0309 0.0466 1.0000 18.000 1.6034 0.06759 0.06262 -0.0308 0.0438 1.0000 18.250 1.6093 0.06972 0.06483 -0.0308 0.0421 1.0000 18.500 1.6103 0.07245 0.06758 -0.0309 0.0388 1.0000 18.750 1.6106 0.07530 0.07046 -0.0310 0.0357 1.0000 19.000 1.6060 0.07885 0.07401 -0.0313 0.0309 1.0000