XFOIL Version 6.94 Calculated polar for: FX 83-W-108 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 0.4865 0.01031 0.00433 -0.1233 0.7987 0.5406 0.500 0.5378 0.01015 0.00417 -0.1219 0.7865 0.5628 1.000 0.5856 0.00974 0.00391 -0.1195 0.7668 0.6311 2.000 0.7742 0.00904 0.00400 -0.1357 0.7417 1.0000 2.500 0.8231 0.00910 0.00399 -0.1341 0.7260 1.0000 3.000 0.8674 0.00918 0.00404 -0.1311 0.7069 1.0000 3.500 0.9149 0.00929 0.00409 -0.1287 0.6855 1.0000 4.000 0.9646 0.00957 0.00449 -0.1276 0.6787 1.0000 4.500 0.9964 0.00960 0.00431 -0.1214 0.6132 1.0000 5.000 1.0356 0.01000 0.00457 -0.1176 0.5685 1.0000 5.500 1.0705 0.01060 0.00494 -0.1132 0.5092 1.0000 6.000 1.0847 0.01198 0.00575 -0.1052 0.3986 1.0000 6.500 1.0897 0.01418 0.00715 -0.0962 0.2543 1.0000 7.000 1.1045 0.01646 0.00871 -0.0896 0.1434 1.0000 7.500 1.1178 0.01900 0.01035 -0.0838 0.0465 1.0000 8.000 1.1605 0.01969 0.01177 -0.0816 0.0879 1.0000 8.500 1.1948 0.02084 0.01284 -0.0793 0.0718 1.0000 9.000 1.2302 0.02210 0.01383 -0.0767 0.0496 1.0000 10.000 1.2918 0.02516 0.01704 -0.0713 0.0378 1.0000 10.500 1.2961 0.02900 0.02123 -0.0653 0.0378 1.0000 11.500 1.3284 0.03642 0.02931 -0.0562 0.0361 1.0000 12.000 1.3703 0.03583 0.02858 -0.0573 0.0294 1.0000 12.500 1.4049 0.03707 0.02980 -0.0565 0.0214 1.0000 13.000 1.4302 0.03938 0.03207 -0.0546 0.0128 1.0000 13.500 1.4183 0.04544 0.03869 -0.0502 0.0202 1.0000 14.000 1.4260 0.04971 0.04313 -0.0484 0.0174 1.0000 14.500 1.4249 0.05500 0.04882 -0.0460 0.0173 1.0000 15.000 1.4428 0.05875 0.05253 -0.0457 0.0090 1.0000 17.000 1.3786 0.09356 0.08876 -0.0492 0.0096 1.0000 17.500 1.3630 0.10393 0.09947 -0.0532 0.0091 1.0000 18.000 1.3751 0.10913 0.10491 -0.0555 0.0110 1.0000 18.500 1.3100 0.12943 0.12579 -0.0657 0.0111 1.0000 19.500 1.2207 0.16976 0.16647 -0.0911 0.0050 1.0000