XFOIL Version 6.94 Calculated polar for: WORTMANN FX 057-816 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 0.4106 0.02014 0.01284 -0.0699 0.5748 0.0681 0.500 0.4629 0.02063 0.01343 -0.0702 0.5729 0.0818 1.000 0.5060 0.01910 0.01417 -0.0696 0.5714 0.7983 1.500 0.5522 0.01992 0.01505 -0.0675 0.5701 0.8448 2.000 0.5975 0.02046 0.01561 -0.0651 0.5691 0.8666 2.500 0.6429 0.02088 0.01604 -0.0629 0.5678 0.8835 3.000 0.6871 0.02169 0.01684 -0.0609 0.5666 0.8976 3.500 0.6779 0.02597 0.02149 -0.0555 0.5552 0.9092 4.000 0.7208 0.02618 0.02171 -0.0533 0.5537 0.9195 4.500 0.7294 0.02891 0.02455 -0.0495 0.5455 0.9287 5.000 0.9505 0.01118 0.00574 -0.0618 0.4956 0.9265 5.500 0.9496 0.01378 0.00739 -0.0547 0.3086 0.9320 6.000 0.9001 0.01814 0.01161 -0.0430 0.2366 0.9450 6.500 0.8552 0.02446 0.01788 -0.0368 0.1941 0.9637 7.000 0.8198 0.03170 0.02456 -0.0350 0.0729 1.0000 7.500 0.8320 0.03492 0.02758 -0.0337 0.0340 1.0000 8.000 0.8544 0.03763 0.03022 -0.0331 0.0060 1.0000 8.500 0.8849 0.03988 0.03250 -0.0329 0.0063 1.0000 9.000 0.9162 0.04209 0.03477 -0.0328 0.0071 1.0000 9.500 0.9464 0.04439 0.03713 -0.0325 0.0081 1.0000 10.000 0.9748 0.04690 0.03973 -0.0321 0.0088 1.0000 10.500 1.0003 0.04969 0.04263 -0.0316 0.0090 1.0000 11.000 1.0240 0.05268 0.04575 -0.0311 0.0092 1.0000 11.500 1.0437 0.05616 0.04936 -0.0305 0.0091 1.0000 12.000 1.0607 0.06000 0.05332 -0.0300 0.0093 1.0000 12.500 1.0718 0.06464 0.05803 -0.0295 0.0096 1.0000 13.000 1.0817 0.06951 0.06297 -0.0292 0.0097 1.0000 13.500 1.0959 0.07386 0.06733 -0.0288 0.0100 1.0000 14.000 1.1200 0.07695 0.07041 -0.0283 0.0100 1.0000 14.500 1.1450 0.08018 0.07377 -0.0280 0.0092 1.0000 15.000 1.2234 0.07642 0.06966 -0.0250 0.0061 1.0000 15.500 1.0962 0.09168 0.08625 -0.0292 0.0072 1.0000