XFOIL Version 6.94 Calculated polar for: FX 66-S-161 AIRFOIL 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 0.4509 0.01297 0.00565 -0.0928 0.5651 0.6010 0.500 0.5074 0.01310 0.00572 -0.0931 0.5597 0.6120 1.000 0.5638 0.01313 0.00574 -0.0934 0.5539 0.6227 1.500 0.6200 0.01343 0.00600 -0.0937 0.5483 0.6352 2.000 0.6742 0.01352 0.00624 -0.0937 0.5430 0.6502 2.500 0.7292 0.01366 0.00648 -0.0938 0.5378 0.6659 3.000 0.7851 0.01381 0.00668 -0.0940 0.5330 0.6835 3.500 0.8404 0.01423 0.00719 -0.0943 0.5279 0.7074 4.500 0.9413 0.01436 0.00796 -0.0927 0.5167 0.7977 5.000 1.0040 0.01421 0.00818 -0.0940 0.5111 1.0000 5.500 1.0591 0.01481 0.00876 -0.0945 0.5051 1.0000 6.000 1.1093 0.01520 0.00932 -0.0940 0.4985 1.0000 6.500 1.1627 0.01552 0.00972 -0.0939 0.4919 1.0000 7.000 1.2193 0.01607 0.01025 -0.0944 0.4856 1.0000 7.500 1.2647 0.01656 0.01105 -0.0931 0.4787 1.0000 8.000 1.3170 0.01647 0.01105 -0.0925 0.4687 1.0000 8.500 1.3603 0.01557 0.01015 -0.0898 0.4468 1.0000 9.000 1.3950 0.01529 0.00993 -0.0859 0.4202 1.0000 9.500 1.4256 0.01560 0.01040 -0.0817 0.3921 1.0000 10.000 1.4352 0.01644 0.01118 -0.0740 0.3536 1.0000 10.500 1.4167 0.01849 0.01301 -0.0631 0.3021 1.0000 11.000 1.3739 0.02284 0.01707 -0.0525 0.2376 1.0000 11.500 1.3223 0.02991 0.02387 -0.0457 0.1777 1.0000 12.000 1.2738 0.03826 0.03199 -0.0417 0.1248 1.0000 12.500 1.2271 0.04735 0.04079 -0.0393 0.0728 1.0000 13.000 1.1922 0.05629 0.04952 -0.0383 0.0402 1.0000 13.500 1.1796 0.06356 0.05685 -0.0381 0.0318 1.0000 14.000 1.1735 0.07046 0.06387 -0.0385 0.0279 1.0000 14.500 1.1696 0.07735 0.07088 -0.0392 0.0251 1.0000 15.000 1.1674 0.08420 0.07779 -0.0402 0.0229 1.0000 15.500 1.1727 0.09021 0.08395 -0.0411 0.0213 1.0000 16.000 1.1800 0.09577 0.08951 -0.0420 0.0195 1.0000 16.500 1.1917 0.10106 0.09499 -0.0431 0.0177 1.0000 17.500 1.2152 0.11132 0.10536 -0.0456 0.0138 1.0000 18.000 1.2251 0.11712 0.11144 -0.0474 0.0124 1.0000 18.500 1.2418 0.12122 0.11559 -0.0482 0.0112 1.0000 19.000 1.2462 0.12804 0.12277 -0.0507 0.0101 1.0000 19.500 1.2570 0.13327 0.12809 -0.0527 0.0092 1.0000 20.000 1.2487 0.14248 0.13776 -0.0568 0.0086 1.0000 20.500 1.2363 0.15265 0.14836 -0.0620 0.0083 1.0000 21.000 1.2179 0.16427 0.16038 -0.0685 0.0082 1.0000 21.500 1.1928 0.17786 0.17437 -0.0768 0.0081 1.0000 22.000 1.1630 0.19340 0.19027 -0.0867 0.0083 1.0000 22.500 1.1280 0.21177 0.20894 -0.0984 0.0087 1.0000 23.000 1.1017 0.22921 0.22650 -0.1089 0.0090 1.0000 24.500 0.8883 0.32247 0.32062 -0.1512 0.0167 1.0000 25.000 0.8889 0.33623 0.33437 -0.1564 0.0158 1.0000 25.500 0.8952 0.34598 0.34415 -0.1600 0.0146 1.0000 26.000 0.9039 0.35375 0.35196 -0.1627 0.0140 1.0000 26.500 0.9074 0.36574 0.36396 -0.1668 0.0137 1.0000 27.000 0.9121 0.37714 0.37537 -0.1707 0.0126 1.0000 27.500 0.9178 0.38673 0.38499 -0.1740 0.0119 1.0000 28.000 0.9241 0.39529 0.39358 -0.1769 0.0115 1.0000 28.500 0.9288 0.40594 0.40425 -0.1802 0.0113 1.0000 29.000 0.9320 0.41856 0.41688 -0.1842 0.0105 1.0000 29.500 0.9365 0.42845 0.42679 -0.1874 0.0096 1.0000 30.000 0.9416 0.43669 0.43507 -0.1900 0.0091 1.0000 30.500 0.9441 0.44917 0.44756 -0.1936 0.0089 1.0000 31.000 0.9475 0.46065 0.45906 -0.1969 0.0083 1.0000 31.500 0.9507 0.47104 0.46948 -0.2000 0.0076 1.0000 32.000 0.9536 0.48068 0.47914 -0.2029 0.0072 1.0000 33.000 0.9581 0.50113 0.49964 -0.2087 0.0069 1.0000 33.500 0.9599 0.51298 0.51151 -0.2119 0.0068 1.0000 34.000 0.9616 0.52390 0.52246 -0.2147 0.0063 1.0000 34.500 0.9628 0.53397 0.53255 -0.2176 0.0061 1.0000 35.000 0.9636 0.54388 0.54249 -0.2204 0.0058 1.0000 35.500 0.9641 0.55365 0.55229 -0.2231 0.0055 1.0000 36.000 0.9642 0.56297 0.56163 -0.2258 0.0053 1.0000 36.500 0.9638 0.57169 0.57039 -0.2284 0.0051 1.0000 37.500 0.9626 0.59285 0.59159 -0.2338 0.0050 1.0000 38.000 0.9617 0.60271 0.60148 -0.2363 0.0048 1.0000 38.500 0.9605 0.61260 0.61139 -0.2388 0.0044 1.0000 39.000 0.9588 0.62171 0.62053 -0.2412 0.0042 1.0000 39.500 0.9566 0.63052 0.62937 -0.2436 0.0040 1.0000 40.000 0.9541 0.63884 0.63771 -0.2460 0.0037 1.0000 40.500 0.9512 0.64694 0.64584 -0.2484 0.0036 1.0000 41.000 0.9477 0.65429 0.65322 -0.2506 0.0035 1.0000 41.500 0.9440 0.66164 0.66060 -0.2527 0.0034 1.0000 43.000 0.9324 0.68602 0.68505 -0.2593 0.0034 1.0000 43.500 0.9280 0.69321 0.69226 -0.2614 0.0033 1.0000 44.000 0.9234 0.70024 0.69933 -0.2634 0.0033 1.0000 44.500 0.9185 0.70690 0.70601 -0.2653 0.0032 1.0000 45.000 0.9133 0.71322 0.71236 -0.2672 0.0030 1.0000 45.500 0.9075 0.71871 0.71788 -0.2691 0.0029 1.0000 46.000 0.9017 0.72444 0.72362 -0.2709 0.0027 1.0000 46.500 0.8954 0.72935 0.72856 -0.2726 0.0026 1.0000 47.000 0.8890 0.73411 0.73335 -0.2744 0.0024 1.0000 47.500 0.8821 0.73830 0.73757 -0.2761 0.0022 1.0000 48.000 0.8750 0.74193 0.74122 -0.2777 0.0021 1.0000 48.500 0.8675 0.74503 0.74434 -0.2794 0.0021 1.0000 49.000 0.8593 0.74762 0.74696 -0.2809 0.0020 1.0000 51.000 0.8281 0.75907 0.75849 -0.2865 0.0019 1.0000 51.500 0.8198 0.76062 0.76006 -0.2877 0.0019 1.0000 52.000 0.8113 0.76191 0.76137 -0.2889 0.0019 1.0000 52.500 0.8027 0.76314 0.76262 -0.2900 0.0018 1.0000 53.000 0.7937 0.76339 0.76290 -0.2912 0.0018 1.0000 53.500 0.7845 0.76313 0.76265 -0.2922 0.0017 1.0000 54.000 0.7751 0.76261 0.76215 -0.2932 0.0016 1.0000 54.500 0.7655 0.76133 0.76089 -0.2942 0.0014 1.0000 55.000 0.7558 0.75999 0.75957 -0.2952 0.0013 1.0000 55.500 0.7458 0.75796 0.75756 -0.2960 0.0012 1.0000 56.000 0.7358 0.75561 0.75523 -0.2969 0.0011 1.0000 56.500 0.7254 0.75253 0.75216 -0.2977 0.0011 1.0000 57.000 0.7150 0.74903 0.74868 -0.2985 0.0010 1.0000 57.500 0.7041 0.74512 0.74478 -0.2993 0.0009 1.0000