XFOIL Version 6.94 Calculated polar for: CLARK-Y 11.7% smoothed 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 0.5050 0.00847 0.00361 -0.1038 0.7594 0.9890 0.500 0.5834 0.00848 0.00341 -0.1085 0.7371 1.0000 1.000 0.6251 0.00855 0.00332 -0.1055 0.7131 1.0000 1.500 0.6668 0.00865 0.00329 -0.1024 0.6867 1.0000 2.000 0.7095 0.00883 0.00330 -0.0995 0.6608 1.0000 2.500 0.7510 0.00904 0.00340 -0.0964 0.6316 1.0000 3.000 0.7919 0.00931 0.00353 -0.0931 0.5996 1.0000 3.500 0.8321 0.00965 0.00374 -0.0897 0.5658 1.0000 4.000 0.8710 0.01006 0.00399 -0.0860 0.5287 1.0000 4.500 0.9079 0.01057 0.00432 -0.0821 0.4882 1.0000 5.000 0.9427 0.01119 0.00472 -0.0778 0.4457 1.0000 5.500 0.9781 0.01182 0.00518 -0.0737 0.4080 1.0000 6.000 1.0140 0.01248 0.00572 -0.0698 0.3777 1.0000 6.500 1.0509 0.01310 0.00627 -0.0662 0.3521 1.0000 7.000 1.0876 0.01373 0.00688 -0.0626 0.3305 1.0000 7.500 1.1233 0.01438 0.00751 -0.0588 0.3105 1.0000 8.000 1.1559 0.01503 0.00819 -0.0545 0.2918 1.0000 8.500 1.1847 0.01575 0.00890 -0.0497 0.2707 1.0000 9.000 1.2145 0.01647 0.00969 -0.0452 0.2442 1.0000 9.500 1.2359 0.01763 0.01072 -0.0398 0.1961 1.0000 10.000 1.2402 0.01999 0.01262 -0.0326 0.1276 1.0000 10.500 1.2506 0.02231 0.01485 -0.0269 0.1062 1.0000 11.000 1.2617 0.02477 0.01732 -0.0219 0.0946 1.0000 11.500 1.2799 0.02699 0.01970 -0.0182 0.0873 1.0000 12.000 1.2869 0.03016 0.02292 -0.0140 0.0802 1.0000 12.500 1.3040 0.03280 0.02576 -0.0112 0.0749 1.0000 13.000 1.3162 0.03596 0.02903 -0.0086 0.0697 1.0000 13.500 1.3232 0.03975 0.03296 -0.0060 0.0649 1.0000 14.000 1.3355 0.04328 0.03671 -0.0045 0.0604 1.0000 14.500 1.3394 0.04774 0.04124 -0.0031 0.0560 1.0000 15.000 1.3451 0.05234 0.04608 -0.0021 0.0523 1.0000 15.500 1.3492 0.05740 0.05133 -0.0020 0.0485 1.0000 16.000 1.3462 0.06319 0.05717 -0.0015 0.0446 1.0000 16.500 1.3449 0.06965 0.06397 -0.0029 0.0418 1.0000 17.000 1.3409 0.07661 0.07110 -0.0047 0.0387 1.0000 17.500 1.3329 0.08388 0.07846 -0.0060 0.0358 1.0000 18.000 1.3231 0.09228 0.08718 -0.0089 0.0337 1.0000 18.500 1.3135 0.10086 0.09594 -0.0123 0.0313 1.0000 19.000 1.3038 0.10902 0.10415 -0.0150 0.0290 1.0000 19.500 1.2869 0.11936 0.11486 -0.0198 0.0277 1.0000 20.000 1.2715 0.12965 0.12540 -0.0249 0.0261 1.0000 20.500 1.2608 0.13914 0.13504 -0.0299 0.0248 1.0000 21.000 1.2499 0.14827 0.14427 -0.0346 0.0234 1.0000 21.500 1.2196 0.16270 0.15905 -0.0433 0.0229 1.0000 22.000 1.1749 0.18163 0.17836 -0.0553 0.0228 1.0000 23.000 0.7704 0.25484 0.25247 -0.0966 0.0304 1.0000 23.500 0.7907 0.26084 0.25853 -0.0972 0.0292 1.0000 24.000 0.7818 0.27296 0.27064 -0.1043 0.0277 1.0000 24.500 0.7898 0.28063 0.27835 -0.1078 0.0246 1.0000 25.000 0.8023 0.28664 0.28439 -0.1100 0.0236 1.0000 25.500 0.8059 0.29695 0.29473 -0.1141 0.0230 1.0000 26.000 0.8090 0.30692 0.30471 -0.1186 0.0209 1.0000 26.500 0.8168 0.31444 0.31226 -0.1218 0.0194 1.0000 27.000 0.8276 0.32117 0.31905 -0.1240 0.0187 1.0000 27.500 0.8306 0.33149 0.32938 -0.1281 0.0183 1.0000 28.000 0.8341 0.34148 0.33940 -0.1323 0.0160 1.0000 28.500 0.8409 0.34904 0.34699 -0.1354 0.0150 1.0000 29.000 0.8500 0.35697 0.35496 -0.1376 0.0145 1.0000 29.500 0.8505 0.36793 0.36594 -0.1423 0.0141 1.0000 30.000 0.8553 0.37744 0.37548 -0.1457 0.0127 1.0000 30.500 0.8603 0.38549 0.38356 -0.1489 0.0118 1.0000 31.000 0.8656 0.39300 0.39110 -0.1518 0.0114 1.0000 31.500 0.8687 0.40338 0.40152 -0.1552 0.0111 1.0000 32.000 0.8721 0.41356 0.41172 -0.1586 0.0100 1.0000 32.500 0.8758 0.42218 0.42037 -0.1618 0.0092 1.0000 33.000 0.8791 0.43026 0.42849 -0.1649 0.0088 1.0000 33.500 0.8832 0.43786 0.43613 -0.1674 0.0086 1.0000 34.000 0.8841 0.44857 0.44685 -0.1710 0.0084 1.0000 34.500 0.8865 0.45877 0.45709 -0.1742 0.0075 1.0000 35.000 0.8884 0.46738 0.46573 -0.1772 0.0070 1.0000 35.500 0.8900 0.47536 0.47375 -0.1802 0.0066 1.0000 36.000 0.8913 0.48288 0.48130 -0.1831 0.0063 1.0000 36.500 0.8921 0.49392 0.49236 -0.1861 0.0062 1.0000 37.000 0.8929 0.50299 0.50146 -0.1891 0.0059 1.0000 37.500 0.8933 0.51179 0.51029 -0.1919 0.0055 1.0000 38.000 0.8933 0.52004 0.51857 -0.1948 0.0051 1.0000 38.500 0.8929 0.52796 0.52653 -0.1976 0.0048 1.0000 39.000 0.8921 0.53531 0.53392 -0.2004 0.0046 1.0000 40.000 0.8898 0.55269 0.55135 -0.2058 0.0043 1.0000 40.500 0.8884 0.56083 0.55952 -0.2085 0.0042 1.0000 41.000 0.8866 0.56868 0.56740 -0.2111 0.0039 1.0000 41.500 0.8845 0.57628 0.57504 -0.2137 0.0035 1.0000 42.000 0.8818 0.58317 0.58196 -0.2162 0.0033 1.0000 42.500 0.8788 0.58963 0.58845 -0.2188 0.0031 1.0000 44.000 0.8682 0.61005 0.60895 -0.2261 0.0029 1.0000 44.500 0.8646 0.61728 0.61621 -0.2284 0.0028 1.0000 45.000 0.8606 0.62367 0.62264 -0.2306 0.0026 1.0000 45.500 0.8560 0.62928 0.62828 -0.2329 0.0024 1.0000 46.000 0.8511 0.63464 0.63367 -0.2351 0.0022 1.0000 46.500 0.8459 0.63966 0.63872 -0.2373 0.0020 1.0000 47.000 0.8403 0.64416 0.64325 -0.2395 0.0019 1.0000 47.500 0.8340 0.64784 0.64696 -0.2417 0.0018 1.0000 49.000 0.8160 0.66171 0.66090 -0.2475 0.0017 1.0000 49.500 0.8096 0.66566 0.66488 -0.2493 0.0016 1.0000 50.000 0.8029 0.66897 0.66823 -0.2511 0.0015 1.0000 50.500 0.7957 0.67164 0.67092 -0.2529 0.0014 1.0000 51.000 0.7884 0.67419 0.67349 -0.2547 0.0012 1.0000 51.500 0.7807 0.67601 0.67535 -0.2564 0.0011 1.0000 52.000 0.7727 0.67722 0.67658 -0.2580 0.0010 1.0000 52.500 0.7643 0.67802 0.67740 -0.2598 0.0009 1.0000 53.000 0.7556 0.67821 0.67762 -0.2614 0.0009 1.0000 54.000 0.7393 0.68113 0.68059 -0.2641 0.0008 1.0000 54.500 0.7307 0.68121 0.68069 -0.2655 0.0008 1.0000 55.000 0.7220 0.68142 0.68092 -0.2668 0.0008 1.0000 55.500 0.7129 0.68068 0.68020 -0.2680 0.0007 1.0000 56.000 0.7036 0.67932 0.67887 -0.2693 0.0006 1.0000 56.500 0.6941 0.67785 0.67742 -0.2704 0.0005 1.0000 57.000 0.6845 0.67580 0.67539 -0.2716 0.0004 1.0000 57.500 0.6746 0.67321 0.67282 -0.2727 0.0004 1.0000 58.000 0.6645 0.66998 0.66961 -0.2738 0.0003 1.0000 58.500 0.6540 0.66609 0.66575 -0.2749 0.0003 1.0000 60.000 0.6239 0.65688 0.65659 -0.2772 0.0003 1.0000