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 = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.3616 0.00945 0.00430 -0.0733 0.6968 0.9161 0.500 0.4148 0.00953 0.00433 -0.0719 0.6866 0.9550 1.000 0.4972 0.00947 0.00418 -0.0771 0.6743 0.9834 1.500 0.5951 0.00948 0.00401 -0.0860 0.6634 1.0000 2.000 0.6400 0.00965 0.00417 -0.0847 0.6528 1.0000 2.500 0.6856 0.00975 0.00422 -0.0832 0.6405 1.0000 3.000 0.7351 0.01002 0.00440 -0.0822 0.6277 1.0000 3.500 0.7868 0.01018 0.00459 -0.0818 0.6154 1.0000 4.000 0.8413 0.01038 0.00472 -0.0817 0.6025 1.0000 4.500 0.8953 0.01068 0.00506 -0.0817 0.5894 1.0000 5.000 0.9494 0.01084 0.00527 -0.0815 0.5733 1.0000 5.500 1.0032 0.01118 0.00564 -0.0814 0.5582 1.0000 6.000 1.0565 0.01141 0.00590 -0.0811 0.5407 1.0000 6.500 1.1064 0.01158 0.00604 -0.0801 0.5089 1.0000 7.000 1.1557 0.01195 0.00648 -0.0792 0.4793 1.0000 7.500 1.2023 0.01249 0.00698 -0.0779 0.4437 1.0000 8.000 1.2430 0.01333 0.00769 -0.0759 0.3919 1.0000 8.500 1.2731 0.01477 0.00882 -0.0725 0.3190 1.0000 9.000 1.2824 0.01713 0.01070 -0.0666 0.2292 1.0000 9.500 1.2767 0.02074 0.01379 -0.0602 0.1367 1.0000 10.000 1.2676 0.02521 0.01779 -0.0549 0.0710 1.0000 10.500 1.2678 0.02945 0.02201 -0.0510 0.0520 1.0000 11.000 1.2807 0.03290 0.02558 -0.0486 0.0428 1.0000 11.500 1.2793 0.03770 0.03052 -0.0457 0.0374 1.0000 12.000 1.2922 0.04148 0.03447 -0.0440 0.0329 1.0000 12.500 1.2988 0.04600 0.03909 -0.0426 0.0289 1.0000 13.000 1.2940 0.05171 0.04498 -0.0402 0.0275 1.0000 13.500 1.3025 0.05619 0.04972 -0.0383 0.0258 1.0000 14.000 1.3133 0.06090 0.05465 -0.0378 0.0230 1.0000 14.500 1.3196 0.06615 0.06007 -0.0373 0.0206 1.0000 15.000 1.3270 0.07130 0.06545 -0.0364 0.0199 1.0000 15.500 1.3294 0.07718 0.07156 -0.0358 0.0188 1.0000 16.000 1.3212 0.08462 0.07936 -0.0349 0.0179 1.0000 17.000 1.2769 0.10574 0.10133 -0.0406 0.0168 1.0000 17.500 1.2550 0.11723 0.11318 -0.0460 0.0166 1.0000 18.000 1.2288 0.13026 0.12658 -0.0531 0.0165 1.0000 18.500 1.1933 0.14632 0.14300 -0.0630 0.0165 1.0000