XFOIL Version 6.94 Calculated polar for: NASA NLF1015 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.6841 0.01431 0.00868 -0.1737 0.7924 0.7486 0.500 0.7273 0.01477 0.00917 -0.1719 0.7862 0.7583 1.000 0.7778 0.01499 0.00942 -0.1713 0.7803 0.7667 1.500 0.8445 0.01496 0.00935 -0.1741 0.7762 0.7743 2.000 0.8881 0.01532 0.00980 -0.1722 0.7691 0.7807 2.500 0.9468 0.01533 0.00983 -0.1733 0.7623 0.7883 3.000 1.0205 0.01507 0.00957 -0.1771 0.7574 0.7938 3.500 1.0570 0.01530 0.00996 -0.1737 0.7468 0.8017 4.000 1.1350 0.01489 0.00956 -0.1783 0.7404 0.8085 5.500 1.2859 0.01432 0.00939 -0.1752 0.7051 0.8332 6.000 1.3349 0.01401 0.00922 -0.1737 0.6894 0.8433 6.500 1.3506 0.01378 0.00917 -0.1653 0.6642 0.8567 7.000 1.3582 0.01370 0.00917 -0.1553 0.6279 0.8730 7.500 1.3658 0.01416 0.00958 -0.1459 0.5733 0.8927 8.000 1.3538 0.01559 0.01070 -0.1336 0.4945 0.9242 8.500 1.3384 0.01815 0.01287 -0.1228 0.4138 1.0000 9.000 1.3317 0.02180 0.01609 -0.1154 0.3342 1.0000 9.500 1.3253 0.02586 0.01971 -0.1088 0.2526 1.0000 10.000 1.3221 0.03014 0.02354 -0.1033 0.1723 1.0000 10.500 1.3211 0.03465 0.02754 -0.0986 0.0949 1.0000 11.000 1.3131 0.04017 0.03253 -0.0937 0.0269 1.0000 11.500 1.3260 0.04417 0.03665 -0.0908 0.0198 1.0000 12.000 1.3400 0.04821 0.04087 -0.0884 0.0175 1.0000 12.500 1.3436 0.05353 0.04640 -0.0858 0.0162 1.0000 13.000 1.3517 0.05859 0.05167 -0.0837 0.0153 1.0000 13.500 1.3621 0.06358 0.05687 -0.0822 0.0144 1.0000 14.000 1.3712 0.06889 0.06237 -0.0809 0.0137 1.0000 14.500 1.3811 0.07426 0.06794 -0.0798 0.0132 1.0000 15.000 1.3931 0.07955 0.07346 -0.0789 0.0128 1.0000 15.500 1.4061 0.08485 0.07898 -0.0782 0.0125 1.0000 16.000 1.4185 0.09043 0.08485 -0.0776 0.0123 1.0000 16.500 1.4250 0.09706 0.09184 -0.0776 0.0123 1.0000 17.000 1.4213 0.10524 0.10046 -0.0786 0.0123 1.0000 17.500 1.4051 0.11568 0.11144 -0.0811 0.0126 1.0000 18.000 1.3702 0.13007 0.12647 -0.0867 0.0131 1.0000 18.500 1.3257 0.14753 0.14451 -0.0960 0.0137 1.0000 19.000 1.2818 0.16675 0.16417 -0.1084 0.0142 1.0000 19.500 1.2331 0.19029 0.18808 -0.1248 0.0148 1.0000 20.000 1.1972 0.21252 0.21043 -0.1392 0.0161 1.0000