XFOIL Version 6.96 Calculated polar for: E. Bambino 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -7.250 -0.5692 0.10993 0.10687 0.0220 1.0000 0.0085 -7.000 -0.5672 0.10544 0.10242 0.0202 1.0000 0.0086 -6.750 -0.5644 0.10123 0.09823 0.0188 1.0000 0.0088 -6.500 -0.5609 0.09722 0.09425 0.0172 1.0000 0.0090 -6.250 -0.5578 0.09326 0.09032 0.0148 1.0000 0.0091 -6.000 -0.5516 0.08911 0.08618 0.0116 1.0000 0.0093 -5.750 -0.5437 0.08494 0.08200 0.0086 1.0000 0.0095 -5.500 -0.5339 0.08074 0.07779 0.0055 1.0000 0.0097 -5.250 -0.5223 0.07653 0.07355 0.0025 1.0000 0.0100 -5.000 -0.5088 0.07230 0.06928 -0.0004 1.0000 0.0103 -4.750 -0.4935 0.06809 0.06502 -0.0032 1.0000 0.0106 -4.500 -0.4763 0.06393 0.06077 -0.0056 1.0000 0.0110 -4.250 -0.4574 0.05982 0.05657 -0.0078 1.0000 0.0114 -4.000 -0.4368 0.05580 0.05241 -0.0096 1.0000 0.0120 -3.750 -0.4148 0.05188 0.04835 -0.0111 1.0000 0.0126 -3.500 -0.3881 0.04791 0.04420 -0.0130 0.9708 0.0134 -3.250 -0.3580 0.04417 0.04019 -0.0145 0.9326 0.0146 -3.000 -0.3267 0.04216 0.03782 -0.0138 0.8908 0.0161 -2.750 -0.3047 0.03963 0.03491 -0.0124 0.8331 0.0163 -2.250 -0.2699 0.03205 0.02645 -0.0105 0.7142 0.0189 -1.250 -0.1641 0.02425 0.01525 -0.0078 0.1604 0.0208 -1.000 -0.1334 0.02179 0.01235 -0.0067 0.1479 0.0127 -0.750 -0.1038 0.01972 0.00986 -0.0058 0.1349 0.0110 -0.500 -0.0748 0.01824 0.00790 -0.0052 0.0750 0.0101 -0.250 -0.0469 0.01713 0.00649 -0.0046 0.0674 0.0097 0.000 -0.0195 0.01617 0.00539 -0.0041 0.0638 0.0097 0.250 0.0076 0.01536 0.00448 -0.0037 0.0621 0.0107 0.500 0.0350 0.01482 0.00380 -0.0035 0.0612 0.0137 0.750 0.0629 0.01450 0.00327 -0.0032 0.0605 0.0155 1.000 0.0908 0.01421 0.00297 -0.0030 0.0598 0.0396 1.250 0.1077 0.01189 0.00291 -0.0016 0.0588 0.7131 1.500 0.1590 0.01167 0.00314 -0.0051 0.0555 0.9949 1.750 0.1914 0.01193 0.00327 -0.0063 0.0526 1.0000 2.000 0.2163 0.01221 0.00344 -0.0059 0.0508 1.0000 2.250 0.2413 0.01252 0.00367 -0.0055 0.0498 1.0000 2.500 0.2665 0.01283 0.00388 -0.0052 0.0491 1.0000 2.750 0.2920 0.01305 0.00402 -0.0049 0.0486 1.0000 3.000 0.3176 0.01330 0.00422 -0.0046 0.0480 1.0000 3.250 0.3435 0.01359 0.00447 -0.0044 0.0473 1.0000 3.500 0.3693 0.01393 0.00477 -0.0043 0.0465 1.0000 3.750 0.3953 0.01431 0.00513 -0.0041 0.0458 1.0000 4.000 0.4212 0.01473 0.00557 -0.0040 0.0452 1.0000 4.250 0.4471 0.01518 0.00602 -0.0038 0.0446 1.0000 4.500 0.4733 0.01535 0.00619 -0.0039 0.0422 1.0000 4.750 0.4999 0.01529 0.00606 -0.0041 0.0387 1.0000 5.000 0.5280 0.01474 0.00556 -0.0042 0.0313 1.0000 5.250 0.5540 0.01530 0.00616 -0.0040 0.0149 1.0000 5.500 0.5802 0.01574 0.00671 -0.0039 0.0117 1.0000 5.750 0.6066 0.01617 0.00727 -0.0037 0.0105 1.0000 6.000 0.6319 0.01708 0.00839 -0.0035 0.0079 1.0000 6.250 0.6578 0.01768 0.00913 -0.0034 0.0077 1.0000 6.500 0.6836 0.01834 0.00993 -0.0032 0.0076 1.0000 6.750 0.7085 0.01932 0.01104 -0.0030 0.0077 1.0000 7.000 0.7337 0.02009 0.01187 -0.0027 0.0081 1.0000 7.250 0.7587 0.02088 0.01265 -0.0024 0.0083 1.0000 7.500 0.7821 0.02208 0.01387 -0.0020 0.0068 1.0000