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 = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.4607 0.01212 0.00721 -0.0899 0.6765 0.8435 0.500 0.5157 0.01218 0.00718 -0.0900 0.6738 0.8562 1.000 0.5672 0.01247 0.00741 -0.0896 0.6703 0.8661 1.500 0.6120 0.01263 0.00761 -0.0883 0.6659 0.8749 2.000 0.6581 0.01277 0.00778 -0.0870 0.6617 0.8838 2.500 0.7098 0.01286 0.00785 -0.0870 0.6581 0.8912 3.000 0.7664 0.01267 0.00765 -0.0877 0.6550 0.8978 3.500 0.8253 0.01266 0.00763 -0.0890 0.6521 0.9043 4.000 0.8689 0.01305 0.00808 -0.0877 0.6479 0.9115 4.500 0.9074 0.01311 0.00827 -0.0852 0.6414 0.9211 5.000 0.9704 0.01256 0.00774 -0.0870 0.6356 0.9278 5.500 1.0417 0.01224 0.00740 -0.0906 0.6302 0.9336 6.000 1.0922 0.01245 0.00784 -0.0910 0.6226 0.9457 6.500 1.1724 0.01192 0.00736 -0.0966 0.6123 0.9548 7.000 1.2446 0.01153 0.00700 -0.1010 0.5902 0.9780 7.500 1.2653 0.01202 0.00761 -0.0956 0.5766 1.0000 8.000 1.2697 0.01284 0.00844 -0.0876 0.5547 1.0000 8.500 1.2658 0.01500 0.01048 -0.0804 0.5117 1.0000 9.000 1.2631 0.01783 0.01313 -0.0743 0.4638 1.0000 9.500 1.2317 0.02259 0.01749 -0.0656 0.3922 1.0000 10.000 1.2057 0.02775 0.02229 -0.0586 0.3247 1.0000 10.500 1.1794 0.03353 0.02763 -0.0524 0.2464 1.0000 11.000 1.1692 0.03847 0.03221 -0.0481 0.1794 1.0000 11.500 1.1668 0.04300 0.03644 -0.0448 0.1236 1.0000 12.000 1.1562 0.04836 0.04135 -0.0412 0.0546 1.0000 12.500 1.1677 0.05210 0.04503 -0.0393 0.0378 1.0000 13.000 1.1837 0.05554 0.04852 -0.0380 0.0308 1.0000 13.500 1.2007 0.05895 0.05201 -0.0368 0.0232 1.0000 14.000 1.2044 0.06376 0.05672 -0.0352 0.0045 1.0000 14.500 1.2134 0.06817 0.06127 -0.0339 0.0029 1.0000 15.000 1.2221 0.07278 0.06606 -0.0329 0.0025 1.0000 15.500 1.2318 0.07734 0.07080 -0.0321 0.0023 1.0000 16.000 1.2385 0.08233 0.07599 -0.0315 0.0022 1.0000 16.500 1.2415 0.08790 0.08177 -0.0311 0.0021 1.0000 17.000 1.2433 0.09373 0.08779 -0.0310 0.0021 1.0000 17.500 1.2406 0.10026 0.09453 -0.0312 0.0020 1.0000 18.000 1.2366 0.10718 0.10165 -0.0319 0.0020 1.0000 18.500 1.2296 0.11461 0.10930 -0.0329 0.0019 1.0000 19.000 1.2244 0.12193 0.11681 -0.0344 0.0019 1.0000 19.500 1.2185 0.12949 0.12458 -0.0363 0.0019 1.0000 20.000 1.2141 0.13695 0.13225 -0.0387 0.0019 1.0000 20.500 1.2094 0.14454 0.14006 -0.0414 0.0020 1.0000 21.000 1.2038 0.15250 0.14826 -0.0447 0.0020 1.0000 21.500 1.1970 0.16097 0.15699 -0.0488 0.0020 1.0000 22.000 1.1885 0.17012 0.16641 -0.0538 0.0020 1.0000 22.500 1.1766 0.18046 0.17704 -0.0599 0.0021 1.0000 23.000 1.1593 0.19275 0.18967 -0.0677 0.0021 1.0000 23.500 1.1418 0.20605 0.20325 -0.0766 0.0022 1.0000 24.000 1.1192 0.22218 0.21968 -0.0873 0.0023 1.0000 24.500 1.0847 0.24537 0.24314 -0.1013 0.0025 1.0000 26.500 0.8371 0.32869 0.32714 -0.1315 0.0079 1.0000 27.000 0.8402 0.34102 0.33947 -0.1360 0.0077 1.0000 27.500 0.8451 0.35224 0.35071 -0.1400 0.0070 1.0000 28.000 0.8509 0.36175 0.36024 -0.1437 0.0066 1.0000 28.500 0.8566 0.37056 0.36907 -0.1472 0.0062 1.0000 29.000 0.8626 0.37856 0.37710 -0.1505 0.0060 1.0000 29.500 0.8679 0.38804 0.38660 -0.1538 0.0059 1.0000 30.000 0.8708 0.40003 0.39861 -0.1578 0.0057 1.0000 30.500 0.8751 0.41070 0.40929 -0.1614 0.0054 1.0000 31.000 0.8792 0.42055 0.41918 -0.1648 0.0051 1.0000 31.500 0.8829 0.43012 0.42877 -0.1681 0.0048 1.0000 32.000 0.8863 0.43940 0.43807 -0.1714 0.0045 1.0000 32.500 0.8894 0.44729 0.44599 -0.1745 0.0042 1.0000 33.000 0.8923 0.45663 0.45535 -0.1775 0.0041 1.0000 33.500 0.8941 0.46792 0.46666 -0.1809 0.0041 1.0000 34.000 0.8967 0.47903 0.47779 -0.1841 0.0036 1.0000 34.500 0.8986 0.48874 0.48751 -0.1871 0.0032 1.0000 35.000 0.9000 0.49779 0.49658 -0.1901 0.0029 1.0000 35.500 0.9008 0.50619 0.50501 -0.1931 0.0028 1.0000 37.000 0.9017 0.53395 0.53284 -0.2016 0.0026 1.0000 37.500 0.9016 0.54355 0.54246 -0.2045 0.0026 1.0000 38.000 0.9017 0.55357 0.55249 -0.2072 0.0025 1.0000 38.500 0.9009 0.56212 0.56107 -0.2098 0.0025 1.0000 39.000 0.8998 0.57058 0.56956 -0.2124 0.0023 1.0000 39.500 0.8983 0.57880 0.57780 -0.2150 0.0022 1.0000 40.000 0.8965 0.58690 0.58591 -0.2176 0.0021 1.0000 40.500 0.8942 0.59441 0.59345 -0.2201 0.0020 1.0000 41.000 0.8917 0.60195 0.60101 -0.2225 0.0019 1.0000 41.500 0.8888 0.60888 0.60796 -0.2250 0.0018 1.0000 42.000 0.8855 0.61564 0.61475 -0.2273 0.0017 1.0000 42.500 0.8819 0.62185 0.62098 -0.2297 0.0016 1.0000 43.000 0.8777 0.62777 0.62692 -0.2320 0.0015 1.0000 43.500 0.8730 0.63327 0.63245 -0.2341 0.0015 1.0000 44.500 0.8646 0.64726 0.64647 -0.2384 0.0015 1.0000 45.000 0.8597 0.65262 0.65185 -0.2405 0.0015 1.0000 45.500 0.8550 0.65867 0.65792 -0.2425 0.0014 1.0000 46.000 0.8499 0.66385 0.66312 -0.2444 0.0014 1.0000 46.500 0.8444 0.66873 0.66802 -0.2462 0.0014 1.0000 47.000 0.8386 0.67299 0.67230 -0.2481 0.0014 1.0000 47.500 0.8324 0.67674 0.67607 -0.2499 0.0013 1.0000 48.000 0.8262 0.68058 0.67993 -0.2516 0.0012 1.0000 48.500 0.8195 0.68350 0.68287 -0.2533 0.0011 1.0000 49.000 0.8126 0.68643 0.68582 -0.2549 0.0010 1.0000 49.500 0.8054 0.68865 0.68806 -0.2565 0.0010 1.0000 50.000 0.7980 0.69078 0.69022 -0.2581 0.0009 1.0000 50.500 0.7903 0.69224 0.69169 -0.2596 0.0008 1.0000 51.000 0.7824 0.69329 0.69277 -0.2611 0.0008 1.0000 51.500 0.7740 0.69372 0.69321 -0.2626 0.0007 1.0000 52.000 0.7651 0.69353 0.69304 -0.2641 0.0007 1.0000 54.000 0.7311 0.69459 0.69415 -0.2687 0.0006 1.0000 54.500 0.7225 0.69429 0.69387 -0.2697 0.0006 1.0000 55.000 0.7135 0.69301 0.69260 -0.2707 0.0006 1.0000 55.500 0.7043 0.69127 0.69088 -0.2716 0.0006 1.0000 56.000 0.6947 0.68877 0.68840 -0.2725 0.0006 1.0000 56.500 0.6852 0.68637 0.68600 -0.2733 0.0006 1.0000 57.000 0.6754 0.68323 0.68288 -0.2741 0.0005 1.0000 57.500 0.6655 0.67956 0.67923 -0.2748 0.0005 1.0000 58.000 0.6554 0.67566 0.67534 -0.2755 0.0005 1.0000 58.500 0.6452 0.67137 0.67106 -0.2761 0.0004 1.0000 59.000 0.6348 0.66647 0.66617 -0.2767 0.0004 1.0000 59.500 0.6243 0.66138 0.66110 -0.2772 0.0003 1.0000 60.000 0.6137 0.65578 0.65551 -0.2777 0.0003 1.0000