XFOIL Version 6.94 Calculated polar for: FX 67-K-170/17 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 0.3011 0.02031 0.01527 -0.0641 0.6758 0.8842 0.500 0.3497 0.01992 0.01479 -0.0622 0.6741 0.9075 1.000 0.4115 0.01956 0.01432 -0.0635 0.6728 0.9204 1.500 0.4771 0.01941 0.01406 -0.0657 0.6715 0.9315 3.500 0.6476 0.02832 0.02315 -0.0733 0.6332 1.0000 4.000 0.7012 0.02763 0.02242 -0.0729 0.6317 1.0000 4.500 0.7646 0.02660 0.02139 -0.0738 0.6309 1.0000 5.000 0.8324 0.02543 0.02022 -0.0753 0.6305 1.0000 5.500 0.9071 0.02411 0.01894 -0.0778 0.6300 1.0000 6.000 0.9988 0.02195 0.01682 -0.0827 0.6288 1.0000 7.000 1.0191 0.02477 0.01977 -0.0718 0.6065 1.0000 7.500 1.1255 0.02135 0.01645 -0.0778 0.6065 1.0000 8.000 1.1376 0.02254 0.01773 -0.0728 0.5918 1.0000 8.500 1.1825 0.02190 0.01718 -0.0715 0.5766 1.0000 9.000 1.2308 0.02125 0.01658 -0.0706 0.5575 1.0000 9.500 1.2553 0.02236 0.01773 -0.0676 0.5311 1.0000 10.000 1.2663 0.02420 0.01938 -0.0632 0.4760 1.0000 10.500 1.2534 0.02783 0.02250 -0.0566 0.3965 1.0000 11.000 1.2352 0.03268 0.02699 -0.0508 0.3326 1.0000 11.500 1.2249 0.03750 0.03158 -0.0464 0.2764 1.0000 12.000 1.2083 0.04316 0.03691 -0.0421 0.2128 1.0000 12.500 1.1940 0.04892 0.04230 -0.0385 0.1471 1.0000 13.000 1.1785 0.05503 0.04796 -0.0352 0.0791 1.0000 13.500 1.1792 0.05993 0.05270 -0.0332 0.0507 1.0000 14.000 1.1877 0.06428 0.05706 -0.0319 0.0394 1.0000 14.500 1.1953 0.06877 0.06159 -0.0307 0.0298 1.0000 15.000 1.2014 0.07360 0.06636 -0.0298 0.0090 1.0000 15.500 1.1987 0.07956 0.07244 -0.0286 0.0057 1.0000 16.000 1.2035 0.08483 0.07793 -0.0280 0.0050 1.0000 16.500 1.2027 0.09095 0.08427 -0.0277 0.0044 1.0000 17.000 1.1986 0.09760 0.09113 -0.0277 0.0041 1.0000 17.500 1.1959 0.10430 0.09807 -0.0282 0.0039 1.0000 18.000 1.1924 0.11120 0.10520 -0.0290 0.0038 1.0000 18.500 1.1880 0.11832 0.11254 -0.0302 0.0036 1.0000 19.000 1.1860 0.12518 0.11961 -0.0317 0.0036 1.0000 19.500 1.1842 0.13206 0.12670 -0.0335 0.0035 1.0000 20.000 1.1834 0.13885 0.13372 -0.0356 0.0035 1.0000 20.500 1.1821 0.14587 0.14100 -0.0382 0.0035 1.0000 21.000 1.1779 0.15367 0.14909 -0.0416 0.0035 1.0000 21.500 1.1696 0.16266 0.15839 -0.0461 0.0035 1.0000 22.000 1.1578 0.17288 0.16895 -0.0519 0.0036 1.0000 22.500 1.1410 0.18497 0.18138 -0.0595 0.0036 1.0000 23.000 1.1191 0.19944 0.19620 -0.0689 0.0037 1.0000 23.500 1.0970 0.21540 0.21245 -0.0796 0.0039 1.0000 24.000 1.0696 0.23545 0.23271 -0.0921 0.0041 1.0000 24.500 0.8038 0.29256 0.29054 -0.1141 0.0156 1.0000 25.000 0.8176 0.29859 0.29662 -0.1164 0.0151 1.0000 25.500 0.8153 0.31260 0.31061 -0.1224 0.0140 1.0000 26.000 0.8221 0.32152 0.31957 -0.1262 0.0130 1.0000 27.000 0.8339 0.34107 0.33915 -0.1339 0.0119 1.0000 27.500 0.8396 0.35080 0.34892 -0.1377 0.0109 1.0000 28.000 0.8458 0.35959 0.35773 -0.1412 0.0103 1.0000 28.500 0.8544 0.36701 0.36519 -0.1438 0.0100 1.0000 29.000 0.8562 0.37915 0.37734 -0.1484 0.0097 1.0000 29.500 0.8609 0.38952 0.38774 -0.1521 0.0091 1.0000 30.000 0.8656 0.39896 0.39721 -0.1556 0.0085 1.0000 30.500 0.8702 0.40787 0.40615 -0.1589 0.0081 1.0000 31.500 0.8782 0.42665 0.42499 -0.1655 0.0077 1.0000 32.000 0.8813 0.43780 0.43615 -0.1690 0.0074 1.0000 32.500 0.8845 0.44757 0.44596 -0.1723 0.0070 1.0000 33.000 0.8874 0.45688 0.45530 -0.1755 0.0064 1.0000 33.500 0.8898 0.46553 0.46398 -0.1786 0.0061 1.0000 34.500 0.8938 0.48584 0.48433 -0.1849 0.0056 1.0000 35.000 0.8956 0.49576 0.49429 -0.1879 0.0052 1.0000 35.500 0.8968 0.50513 0.50368 -0.1909 0.0048 1.0000 36.000 0.8976 0.51399 0.51256 -0.1938 0.0045 1.0000 36.500 0.8980 0.52242 0.52103 -0.1967 0.0043 1.0000 37.000 0.8981 0.53031 0.52895 -0.1994 0.0042 1.0000 37.500 0.8978 0.53995 0.53861 -0.2023 0.0041 1.0000 38.000 0.8975 0.55014 0.54883 -0.2051 0.0041 1.0000 38.500 0.8969 0.55889 0.55760 -0.2079 0.0040 1.0000 39.000 0.8959 0.56750 0.56624 -0.2105 0.0039 1.0000 39.500 0.8946 0.57580 0.57457 -0.2131 0.0037 1.0000 40.000 0.8929 0.58395 0.58274 -0.2157 0.0035 1.0000 40.500 0.8908 0.59147 0.59030 -0.2182 0.0034 1.0000 41.000 0.8884 0.59906 0.59792 -0.2207 0.0032 1.0000 41.500 0.8856 0.60613 0.60501 -0.2231 0.0032 1.0000 42.000 0.8825 0.61310 0.61201 -0.2255 0.0030 1.0000 42.500 0.8789 0.61938 0.61831 -0.2279 0.0029 1.0000 43.000 0.8749 0.62530 0.62427 -0.2302 0.0028 1.0000 44.500 0.8622 0.64473 0.64377 -0.2367 0.0026 1.0000 45.000 0.8575 0.65021 0.64927 -0.2388 0.0026 1.0000 45.500 0.8528 0.65606 0.65514 -0.2408 0.0025 1.0000 46.000 0.8477 0.66112 0.66023 -0.2427 0.0025 1.0000 46.500 0.8422 0.66590 0.66503 -0.2446 0.0023 1.0000 47.000 0.8364 0.67008 0.66924 -0.2465 0.0022 1.0000 47.500 0.8302 0.67384 0.67303 -0.2483 0.0022 1.0000 48.000 0.8239 0.67752 0.67673 -0.2501 0.0020 1.0000 48.500 0.8172 0.68042 0.67966 -0.2518 0.0019 1.0000 49.000 0.8103 0.68320 0.68247 -0.2535 0.0018 1.0000 49.500 0.8030 0.68527 0.68455 -0.2552 0.0017 1.0000 50.000 0.7956 0.68711 0.68642 -0.2568 0.0016 1.0000 50.500 0.7876 0.68819 0.68753 -0.2584 0.0015 1.0000 51.000 0.7792 0.68911 0.68847 -0.2599 0.0015 1.0000 53.000 0.7474 0.69353 0.69296 -0.2650 0.0014 1.0000 53.500 0.7389 0.69333 0.69277 -0.2661 0.0014 1.0000 54.000 0.7301 0.69251 0.69198 -0.2672 0.0014 1.0000 54.500 0.7213 0.69173 0.69122 -0.2682 0.0013 1.0000 55.000 0.7122 0.69013 0.68964 -0.2692 0.0012 1.0000 55.500 0.7028 0.68814 0.68767 -0.2702 0.0011 1.0000 56.000 0.6932 0.68556 0.68510 -0.2711 0.0011 1.0000 56.500 0.6836 0.68291 0.68247 -0.2720 0.0010 1.0000 57.000 0.6737 0.67959 0.67917 -0.2728 0.0009 1.0000 57.500 0.6637 0.67581 0.67540 -0.2736 0.0009 1.0000 58.000 0.6536 0.67166 0.67127 -0.2743 0.0008 1.0000 58.500 0.6432 0.66699 0.66661 -0.2750 0.0007 1.0000 59.000 0.6326 0.66183 0.66147 -0.2756 0.0007 1.0000 59.500 0.6217 0.65632 0.65598 -0.2763 0.0007 1.0000