XFOIL Version 6.94 Calculated polar for: FX 84-W-127 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 0.3799 0.00758 0.00285 -0.0776 0.6706 0.8644 0.500 0.4302 0.00771 0.00293 -0.0759 0.6589 0.9020 1.000 0.4788 0.00770 0.00296 -0.0738 0.6493 0.9358 1.500 0.5353 0.00770 0.00291 -0.0734 0.6385 0.9717 2.000 0.6180 0.00784 0.00295 -0.0791 0.6268 0.9910 2.500 0.6924 0.00785 0.00295 -0.0835 0.6144 1.0000 3.000 0.7387 0.00805 0.00307 -0.0821 0.6013 1.0000 3.500 0.7899 0.00823 0.00325 -0.0816 0.5897 1.0000 4.000 0.8441 0.00841 0.00340 -0.0815 0.5764 1.0000 4.500 0.8988 0.00869 0.00364 -0.0816 0.5617 1.0000 5.000 0.9537 0.00888 0.00392 -0.0817 0.5469 1.0000 5.500 1.0073 0.00919 0.00418 -0.0816 0.5278 1.0000 6.000 1.0597 0.00951 0.00444 -0.0812 0.5028 1.0000 6.500 1.1107 0.00988 0.00478 -0.0807 0.4712 1.0000 7.000 1.1599 0.01042 0.00529 -0.0800 0.4371 1.0000 7.500 1.2060 0.01114 0.00590 -0.0788 0.3891 1.0000 8.000 1.2434 0.01239 0.00685 -0.0766 0.3202 1.0000 8.500 1.2665 0.01447 0.00840 -0.0725 0.2257 1.0000 9.000 1.2763 0.01698 0.01043 -0.0669 0.1429 1.0000 9.500 1.2781 0.02026 0.01328 -0.0613 0.0732 1.0000 10.000 1.2917 0.02310 0.01606 -0.0577 0.0486 1.0000 10.500 1.3037 0.02627 0.01924 -0.0545 0.0371 1.0000 11.000 1.3195 0.02934 0.02238 -0.0520 0.0298 1.0000 11.500 1.3185 0.03405 0.02730 -0.0489 0.0264 1.0000 12.000 1.3363 0.03716 0.03056 -0.0471 0.0246 1.0000 12.500 1.3553 0.04022 0.03371 -0.0459 0.0212 1.0000 13.000 1.3523 0.04577 0.03955 -0.0439 0.0215 1.0000 13.500 1.3580 0.05064 0.04456 -0.0428 0.0195 1.0000 14.000 1.3443 0.05760 0.05175 -0.0410 0.0165 1.0000 14.500 1.3512 0.06280 0.05714 -0.0406 0.0153 1.0000 15.000 1.3569 0.06819 0.06275 -0.0401 0.0150 1.0000 15.500 1.3616 0.07406 0.06883 -0.0407 0.0139 1.0000 16.000 1.3578 0.08081 0.07586 -0.0403 0.0133 1.0000 16.500 1.3618 0.08706 0.08224 -0.0423 0.0125 1.0000 17.000 1.3557 0.09476 0.09023 -0.0438 0.0121 1.0000 17.500 1.3471 0.10317 0.09892 -0.0461 0.0119 1.0000 18.000 1.3361 0.11231 0.10833 -0.0493 0.0116 1.0000 18.500 1.3213 0.12252 0.11881 -0.0537 0.0113 1.0000 19.000 1.2977 0.13479 0.13143 -0.0598 0.0114 1.0000 19.500 1.2730 0.14795 0.14489 -0.0673 0.0112 1.0000 20.000 1.2448 0.16219 0.15944 -0.0767 0.0111 1.0000