XFOIL Version 6.96 Calculated polar for: GOE 647 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -17.750 -0.7154 0.09961 0.09703 -0.0638 1.0000 0.0207 -17.500 -0.7438 0.09144 0.08877 -0.0685 1.0000 0.0208 -17.250 -0.7727 0.08350 0.08072 -0.0732 1.0000 0.0209 -17.000 -0.7969 0.07662 0.07377 -0.0772 1.0000 0.0211 -16.750 -0.8244 0.06972 0.06677 -0.0813 1.0000 0.0211 -16.500 -0.8539 0.06299 0.05994 -0.0852 1.0000 0.0211 -16.250 -0.8864 0.05608 0.05293 -0.0891 1.0000 0.0212 -16.000 -0.9175 0.04955 0.04630 -0.0927 1.0000 0.0212 -15.750 -0.9434 0.04371 0.04036 -0.0957 1.0000 0.0213 -15.250 -0.9603 0.03080 0.02714 -0.1110 0.9967 0.0214 -15.000 -0.9503 0.02776 0.02398 -0.1155 0.9892 0.0216 -14.500 -0.9191 0.02486 0.02091 -0.1175 0.9745 0.0220 -14.250 -0.8956 0.02376 0.01974 -0.1187 0.9688 0.0222 -14.000 -0.8700 0.02274 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0.5715 0.00976 0.00255 -0.0868 0.3177 0.2705 0.750 0.5966 0.00983 0.00261 -0.0861 0.3125 0.2820 1.000 0.6221 0.00986 0.00266 -0.0856 0.3087 0.2947 1.250 0.6472 0.00991 0.00273 -0.0849 0.3041 0.3086 1.500 0.6717 0.00998 0.00280 -0.0842 0.2995 0.3264 1.750 0.6961 0.01002 0.00289 -0.0834 0.2956 0.3510 2.000 0.7209 0.01003 0.00296 -0.0827 0.2930 0.3768 2.250 0.7455 0.01007 0.00305 -0.0820 0.2900 0.4002 2.500 0.7697 0.01012 0.00315 -0.0812 0.2868 0.4244 2.750 0.7934 0.01019 0.00325 -0.0803 0.2835 0.4503 3.000 0.8168 0.01028 0.00336 -0.0794 0.2800 0.4702 3.250 0.8408 0.01034 0.00346 -0.0786 0.2778 0.4879 3.500 0.8645 0.01039 0.00356 -0.0777 0.2753 0.5066 3.750 0.8873 0.01044 0.00367 -0.0767 0.2725 0.5304 4.000 0.9079 0.01046 0.00379 -0.0753 0.2694 0.5713 4.250 0.9195 0.01019 0.00395 -0.0720 0.2665 0.7376 4.750 1.0613 0.01039 0.00460 -0.0908 0.2595 1.0000 5.000 1.0832 0.01053 0.00473 -0.0896 0.2574 1.0000 5.250 1.1048 0.01069 0.00487 -0.0884 0.2551 1.0000 5.500 1.1254 0.01086 0.00503 -0.0870 0.2527 1.0000 5.750 1.1442 0.01104 0.00519 -0.0852 0.2502 1.0000 6.000 1.1623 0.01123 0.00536 -0.0834 0.2477 1.0000 6.250 1.1820 0.01139 0.00552 -0.0818 0.2462 1.0000 6.500 1.2022 0.01155 0.00569 -0.0804 0.2448 1.0000 6.750 1.2224 0.01172 0.00587 -0.0790 0.2432 1.0000 7.000 1.2427 0.01191 0.00606 -0.0777 0.2412 1.0000 7.250 1.2626 0.01212 0.00627 -0.0763 0.2389 1.0000 7.500 1.2825 0.01235 0.00649 -0.0750 0.2369 1.0000 7.750 1.3019 0.01261 0.00674 -0.0737 0.2346 1.0000 8.000 1.3210 0.01289 0.00702 -0.0723 0.2323 1.0000 8.250 1.3412 0.01314 0.00728 -0.0711 0.2309 1.0000 8.500 1.3618 0.01338 0.00755 -0.0701 0.2299 1.0000 8.750 1.3822 0.01363 0.00782 -0.0690 0.2286 1.0000 9.000 1.4023 0.01391 0.00812 -0.0680 0.2272 1.0000 9.250 1.4220 0.01420 0.00844 -0.0669 0.2258 1.0000 9.500 1.4415 0.01453 0.00877 -0.0658 0.2241 1.0000 9.750 1.4602 0.01489 0.00915 -0.0647 0.2224 1.0000 10.000 1.4786 0.01528 0.00955 -0.0636 0.2206 1.0000 10.250 1.4959 0.01573 0.01001 -0.0623 0.2183 1.0000 10.500 1.5131 0.01620 0.01050 -0.0612 0.2163 1.0000 10.750 1.5327 0.01657 0.01090 -0.0603 0.2149 1.0000 11.000 1.5516 0.01698 0.01134 -0.0594 0.2126 1.0000 11.250 1.5695 0.01745 0.01184 -0.0585 0.2106 1.0000 11.500 1.5862 0.01800 0.01240 -0.0574 0.2080 1.0000 11.750 1.6023 0.01859 0.01301 -0.0563 0.2059 1.0000 12.000 1.6158 0.01935 0.01377 -0.0551 0.2020 1.0000 12.250 1.6336 0.01988 0.01435 -0.0543 0.2001 1.0000 12.500 1.6497 0.02053 0.01501 -0.0534 0.1960 1.0000 12.750 1.6632 0.02134 0.01584 -0.0523 0.1923 1.0000 13.000 1.6750 0.02229 0.01679 -0.0511 0.1886 1.0000 13.250 1.6903 0.02303 0.01758 -0.0503 0.1867 1.0000 13.500 1.7045 0.02386 0.01844 -0.0494 0.1834 1.0000 13.750 1.7152 0.02494 0.01953 -0.0484 0.1787 1.0000 14.000 1.7242 0.02617 0.02077 -0.0473 0.1744 1.0000 14.250 1.7347 0.02733 0.02196 -0.0463 0.1688 1.0000 14.500 1.7392 0.02898 0.02358 -0.0451 0.1617 1.0000 14.750 1.7465 0.03045 0.02508 -0.0441 0.1559 1.0000 15.000 1.7451 0.03267 0.02728 -0.0429 0.1458 1.0000 15.250 1.7353 0.03574 0.03029 -0.0414 0.1320 1.0000 15.500 1.7247 0.03900 0.03353 -0.0402 0.1206 1.0000 15.750 1.7119 0.04266 0.03717 -0.0393 0.1101 1.0000 16.000 1.7013 0.04622 0.04075 -0.0386 0.1029 1.0000 16.250 1.6893 0.05006 0.04462 -0.0381 0.0958 1.0000 16.500 1.6761 0.05416 0.04875 -0.0379 0.0887 1.0000 16.750 1.6571 0.05903 0.05365 -0.0378 0.0817 1.0000 17.000 1.6396 0.06390 0.05857 -0.0380 0.0763 1.0000 17.250 1.6248 0.06856 0.06330 -0.0383 0.0716 1.0000 17.500 1.5994 0.07466 0.06946 -0.0390 0.0657 1.0000 17.750 1.5809 0.08007 0.07495 -0.0398 0.0617 1.0000 18.000 1.5567 0.08629 0.08125 -0.0409 0.0574 1.0000 18.250 1.5327 0.09267 0.08771 -0.0421 0.0535 1.0000 18.500 1.5092 0.09911 0.09423 -0.0436 0.0502 1.0000 18.750 1.4777 0.10674 0.10194 -0.0455 0.0447 1.0000 19.000 1.4514 0.11381 0.10908 -0.0474 0.0404 1.0000