XFOIL Version 6.94 Calculated polar for: NASA SC(2)-0518 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.4032 0.01050 0.00552 -0.1027 0.7404 0.6458 0.500 0.4661 0.01047 0.00539 -0.1039 0.7142 0.6508 1.000 0.5241 0.01054 0.00541 -0.1037 0.6818 0.6535 1.500 0.5831 0.01067 0.00539 -0.1040 0.6395 0.6571 2.000 0.6397 0.01102 0.00540 -0.1039 0.5551 0.6609 2.500 0.6803 0.01248 0.00598 -0.1011 0.3740 0.6636 3.000 0.7278 0.01368 0.00659 -0.0998 0.2620 0.6676 3.500 0.7784 0.01461 0.00712 -0.0990 0.1931 0.6715 4.000 0.8285 0.01540 0.00772 -0.0979 0.1563 0.6743 4.500 0.8807 0.01609 0.00826 -0.0972 0.1339 0.6780 5.000 0.9314 0.01683 0.00886 -0.0963 0.1191 0.6815 5.500 0.9801 0.01755 0.00955 -0.0949 0.1089 0.6846 6.000 1.0294 0.01829 0.01029 -0.0937 0.1013 0.6890 6.500 1.0762 0.01902 0.01107 -0.0919 0.0952 0.6926 7.000 1.1181 0.02002 0.01204 -0.0895 0.0894 0.6965 7.500 1.1635 0.02072 0.01280 -0.0876 0.0849 0.7011 8.000 1.1940 0.02179 0.01388 -0.0831 0.0805 0.7051 8.500 1.2335 0.02281 0.01497 -0.0804 0.0766 0.7105 9.000 1.2710 0.02389 0.01610 -0.0776 0.0723 0.7146 10.000 1.3400 0.02671 0.01916 -0.0718 0.0653 0.7250 10.500 1.3730 0.02828 0.02077 -0.0690 0.0622 0.7310 11.000 1.3961 0.03065 0.02323 -0.0653 0.0592 0.7362 11.500 1.4276 0.03241 0.02515 -0.0628 0.0572 0.7422 12.000 1.4550 0.03454 0.02744 -0.0602 0.0550 0.7487 12.500 1.4789 0.03696 0.02999 -0.0575 0.0532 0.7546 13.000 1.4972 0.04004 0.03316 -0.0548 0.0515 0.7614 13.500 1.5048 0.04427 0.03756 -0.0513 0.0497 0.7674 14.000 1.5222 0.04757 0.04108 -0.0493 0.0492 0.7739 14.500 1.5360 0.05138 0.04509 -0.0475 0.0485 0.7810 15.000 1.5457 0.05571 0.04968 -0.0460 0.0479 0.7874 15.500 1.5517 0.06066 0.05488 -0.0449 0.0471 0.7938 16.000 1.5545 0.06630 0.06075 -0.0446 0.0463 0.8009 16.500 1.5530 0.07266 0.06737 -0.0448 0.0456 0.8069 17.000 1.5482 0.07987 0.07482 -0.0461 0.0448 0.8130 17.500 1.5402 0.08798 0.08316 -0.0485 0.0441 0.8197 18.000 1.5278 0.09699 0.09244 -0.0519 0.0433 0.8248 18.500 1.5133 0.10697 0.10264 -0.0567 0.0426 0.8309 19.000 1.4928 0.11817 0.11408 -0.0630 0.0416 0.8358 19.500 1.4405 0.13572 0.13202 -0.0749 0.0403 0.8398