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 = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.7409 0.01055 0.00528 -0.1853 0.7702 0.7177 0.500 0.7947 0.01067 0.00544 -0.1853 0.7652 0.7257 1.000 0.8539 0.01078 0.00553 -0.1864 0.7606 0.7341 1.500 0.9114 0.01094 0.00569 -0.1872 0.7554 0.7405 2.000 0.9620 0.01100 0.00584 -0.1865 0.7484 0.7463 2.500 1.0238 0.01101 0.00583 -0.1882 0.7421 0.7529 3.000 1.0733 0.01108 0.00600 -0.1872 0.7340 0.7585 3.500 1.1307 0.01105 0.00602 -0.1878 0.7260 0.7650 4.000 1.1802 0.01111 0.00617 -0.1869 0.7162 0.7720 4.500 1.2372 0.01105 0.00617 -0.1873 0.7062 0.7782 5.000 1.2803 0.01104 0.00631 -0.1849 0.6937 0.7866 5.500 1.3207 0.01095 0.00633 -0.1817 0.6759 0.7945 6.000 1.3438 0.01091 0.00637 -0.1749 0.6465 0.8045 6.500 1.3618 0.01117 0.00665 -0.1671 0.6089 0.8150 7.000 1.3605 0.01224 0.00745 -0.1561 0.5331 0.8287 7.500 1.3477 0.01434 0.00919 -0.1440 0.4511 0.8445 8.000 1.3310 0.01716 0.01164 -0.1325 0.3663 0.8632 8.500 1.3206 0.02023 0.01439 -0.1232 0.2869 0.8881 9.000 1.3110 0.02285 0.01684 -0.1140 0.2222 0.9775 9.500 1.3139 0.02669 0.02019 -0.1090 0.1406 1.0000 10.000 1.3162 0.03081 0.02382 -0.1043 0.0660 1.0000 10.500 1.3187 0.03519 0.02786 -0.0998 0.0183 1.0000 11.000 1.3394 0.03826 0.03103 -0.0972 0.0143 1.0000 11.500 1.3577 0.04165 0.03456 -0.0947 0.0126 1.0000 12.000 1.3689 0.04585 0.03894 -0.0920 0.0115 1.0000 12.500 1.3838 0.04986 0.04315 -0.0899 0.0109 1.0000 13.000 1.3937 0.05455 0.04804 -0.0877 0.0105 1.0000 13.500 1.4017 0.05964 0.05333 -0.0859 0.0102 1.0000 14.000 1.4085 0.06510 0.05898 -0.0844 0.0098 1.0000 14.500 1.4153 0.07076 0.06485 -0.0832 0.0095 1.0000 15.000 1.4220 0.07662 0.07093 -0.0824 0.0093 1.0000 15.500 1.4292 0.08259 0.07712 -0.0818 0.0091 1.0000 16.000 1.4360 0.08876 0.08352 -0.0815 0.0089 1.0000 16.500 1.4412 0.09534 0.09039 -0.0816 0.0089 1.0000 17.000 1.4418 0.10278 0.09817 -0.0823 0.0089 1.0000 17.500 1.4348 0.11166 0.10747 -0.0840 0.0091 1.0000 18.000 1.4145 0.12318 0.11952 -0.0874 0.0094 1.0000 18.500 1.3793 0.13818 0.13507 -0.0941 0.0099 1.0000 19.000 1.3440 0.15426 0.15160 -0.1033 0.0102 1.0000 19.500 1.3049 0.17262 0.17035 -0.1154 0.0106 1.0000 20.000 1.2630 0.19408 0.19213 -0.1304 0.0109 1.0000 20.500 1.2400 0.21134 0.20955 -0.1419 0.0119 1.0000