XFOIL Version 6.96 Calculated polar for: GOE 646 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.500 -0.8181 0.10661 0.10281 -0.0766 1.0000 0.0407 -19.250 -0.8367 0.10035 0.09641 -0.0800 1.0000 0.0409 -19.000 -0.8510 0.09506 0.09100 -0.0827 1.0000 0.0412 -18.750 -0.8478 0.09288 0.08884 -0.0831 1.0000 0.0417 -18.500 -0.8473 0.09011 0.08606 -0.0840 1.0000 0.0421 -18.250 -0.8483 0.08712 0.08304 -0.0851 1.0000 0.0424 -18.000 -0.8510 0.08388 0.07977 -0.0864 1.0000 0.0429 -17.750 -0.8550 0.08048 0.07633 -0.0877 1.0000 0.0433 -17.500 -0.8599 0.07705 0.07285 -0.0890 1.0000 0.0437 -17.250 -0.8661 0.07352 0.06925 -0.0903 1.0000 0.0442 -17.000 -0.8731 0.06998 0.06564 -0.0916 1.0000 0.0447 -16.750 -0.8796 0.06666 0.06224 -0.0926 1.0000 0.0450 -16.500 -0.8864 0.06346 0.05897 -0.0935 1.0000 0.0453 -16.250 -0.8955 0.06012 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3.250 0.8327 0.01054 0.00421 -0.1062 0.5228 0.5422 3.500 0.8527 0.01059 0.00433 -0.1045 0.5163 0.5785 3.750 0.8700 0.01057 0.00444 -0.1022 0.5098 0.6125 4.000 0.8885 0.01062 0.00455 -0.1002 0.5031 0.6416 4.250 0.9079 0.01074 0.00469 -0.0984 0.4968 0.6664 4.500 0.9270 0.01078 0.00482 -0.0965 0.4905 0.6881 4.750 0.9453 0.01086 0.00495 -0.0945 0.4836 0.7092 5.000 0.9633 0.01095 0.00510 -0.0925 0.4768 0.7330 5.250 0.9798 0.01094 0.00526 -0.0901 0.4690 0.7680 5.500 1.0071 0.01084 0.00550 -0.0900 0.4600 0.9017 5.750 1.0619 0.01107 0.00575 -0.0959 0.4470 1.0000 6.000 1.0792 0.01129 0.00593 -0.0940 0.4361 1.0000 6.250 1.0939 0.01158 0.00614 -0.0916 0.4230 1.0000 6.500 1.1087 0.01190 0.00639 -0.0892 0.4075 1.0000 6.750 1.1231 0.01227 0.00669 -0.0869 0.3914 1.0000 7.000 1.1357 0.01273 0.00705 -0.0843 0.3748 1.0000 7.250 1.1493 0.01320 0.00744 -0.0820 0.3606 1.0000 7.500 1.1627 0.01371 0.00788 -0.0798 0.3487 1.0000 7.750 1.1767 0.01424 0.00834 -0.0776 0.3378 1.0000 8.000 1.1927 0.01471 0.00878 -0.0759 0.3292 1.0000 8.250 1.2075 0.01525 0.00928 -0.0740 0.3209 1.0000 8.500 1.2233 0.01577 0.00978 -0.0724 0.3136 1.0000 8.750 1.2398 0.01628 0.01027 -0.0709 0.3065 1.0000 9.000 1.2524 0.01698 0.01092 -0.0689 0.2991 1.0000 9.250 1.2714 0.01742 0.01139 -0.0678 0.2932 1.0000 9.500 1.2860 0.01806 0.01201 -0.0663 0.2865 1.0000 9.750 1.3003 0.01874 0.01267 -0.0647 0.2804 1.0000 10.000 1.3178 0.01929 0.01325 -0.0636 0.2741 1.0000 10.250 1.3312 0.02006 0.01399 -0.0620 0.2674 1.0000 10.500 1.3463 0.02076 0.01470 -0.0607 0.2619 1.0000 10.750 1.3622 0.02144 0.01540 -0.0596 0.2558 1.0000 11.000 1.3740 0.02236 0.01629 -0.0581 0.2494 1.0000 11.250 1.3891 0.02313 0.01710 -0.0569 0.2433 1.0000 11.500 1.4027 0.02400 0.01798 -0.0557 0.2368 1.0000 11.750 1.4126 0.02513 0.01908 -0.0542 0.2305 1.0000 12.000 1.4277 0.02595 0.01995 -0.0533 0.2247 1.0000 12.250 1.4376 0.02715 0.02113 -0.0519 0.2183 1.0000 12.500 1.4490 0.02827 0.02227 -0.0508 0.2121 1.0000 12.750 1.4600 0.02945 0.02347 -0.0497 0.2061 1.0000 13.000 1.4667 0.03097 0.02496 -0.0484 0.2004 1.0000 13.250 1.4790 0.03211 0.02616 -0.0475 0.1951 1.0000 13.500 1.4871 0.03362 0.02767 -0.0464 0.1894 1.0000 13.750 1.4935 0.03527 0.02933 -0.0454 0.1842 1.0000 14.000 1.5030 0.03673 0.03083 -0.0445 0.1785 1.0000 14.250 1.5071 0.03867 0.03277 -0.0435 0.1728 1.0000 14.500 1.5146 0.04036 0.03449 -0.0427 0.1673 1.0000 14.750 1.5188 0.04239 0.03654 -0.0419 0.1611 1.0000 15.000 1.5218 0.04456 0.03872 -0.0411 0.1549 1.0000 15.250 1.5250 0.04675 0.04093 -0.0404 0.1478 1.0000 15.500 1.5262 0.04917 0.04337 -0.0398 0.1402 1.0000 15.750 1.5229 0.05211 0.04629 -0.0391 0.1306 1.0000 16.000 1.5191 0.05514 0.04930 -0.0386 0.1201 1.0000 16.250 1.5129 0.05846 0.05259 -0.0381 0.1092 1.0000 16.500 1.5062 0.06190 0.05601 -0.0377 0.1006 1.0000 16.750 1.4992 0.06542 0.05954 -0.0374 0.0946 1.0000 17.000 1.4906 0.06917 0.06330 -0.0372 0.0907 1.0000 17.250 1.4862 0.07252 0.06670 -0.0371 0.0880 1.0000 17.500 1.4817 0.07590 0.07013 -0.0371 0.0858 1.0000 17.750 1.4737 0.07975 0.07402 -0.0372 0.0837 1.0000 18.000 1.4639 0.08384 0.07814 -0.0375 0.0819 1.0000 18.250 1.4623 0.08698 0.08136 -0.0377 0.0806 1.0000 18.500 1.4591 0.09035 0.08481 -0.0380 0.0794 1.0000 18.750 1.4565 0.09367 0.08819 -0.0383 0.0781 1.0000 19.000 1.4518 0.09726 0.09184 -0.0388 0.0771 1.0000 19.250 1.4465 0.10092 0.09554 -0.0394 0.0759 1.0000