XFOIL Version 6.96 Calculated polar for: GOE 683 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 ------ -------- --------- --------- -------- -------- -------- -19.750 -0.9670 0.08817 0.08409 -0.0697 1.0000 0.0448 -19.500 -0.9735 0.08398 0.07985 -0.0719 1.0000 0.0451 -19.250 -0.9777 0.08014 0.07596 -0.0740 1.0000 0.0456 -19.000 -0.9865 0.07573 0.07145 -0.0763 1.0000 0.0459 -18.750 -0.9938 0.07158 0.06723 -0.0786 1.0000 0.0463 -18.500 -1.0025 0.06736 0.06290 -0.0807 1.0000 0.0467 -18.250 -1.0105 0.06336 0.05879 -0.0826 1.0000 0.0471 -18.000 -1.0190 0.05942 0.05473 -0.0844 1.0000 0.0476 -17.750 -1.0259 0.05584 0.05102 -0.0858 1.0000 0.0480 -17.500 -1.0315 0.05253 0.04758 -0.0870 1.0000 0.0484 -17.250 -1.0358 0.04952 0.04444 -0.0877 1.0000 0.0487 -17.000 -1.0409 0.04663 0.04140 -0.0883 1.0000 0.0491 -16.750 -1.0382 0.04454 0.03929 -0.0880 1.0000 0.0497 -16.500 -1.0341 0.04267 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0.9313 2.750 0.6522 0.01307 0.00725 -0.0452 0.4308 0.9401 3.000 0.6967 0.01332 0.00742 -0.0485 0.4249 0.9421 3.250 0.7394 0.01360 0.00764 -0.0516 0.4193 0.9454 3.500 0.7625 0.01390 0.00797 -0.0505 0.4151 0.9538 3.750 0.8108 0.01399 0.00803 -0.0547 0.4102 0.9558 4.000 0.8540 0.01414 0.00812 -0.0579 0.4056 0.9590 4.250 0.8852 0.01437 0.00831 -0.0588 0.4012 0.9639 4.500 0.9133 0.01447 0.00845 -0.0589 0.3977 0.9684 4.750 0.9511 0.01444 0.00842 -0.0611 0.3931 0.9705 5.000 0.9862 0.01451 0.00845 -0.0628 0.3887 0.9738 5.250 1.0151 0.01486 0.00875 -0.0632 0.3836 0.9807 5.500 1.0613 0.01460 0.00854 -0.0672 0.3795 0.9837 5.750 1.0986 0.01455 0.00850 -0.0694 0.3754 0.9876 6.000 1.1332 0.01464 0.00856 -0.0711 0.3708 0.9929 6.250 1.1715 0.01454 0.00840 -0.0736 0.3661 0.9961 6.500 1.2139 0.01428 0.00821 -0.0769 0.3620 1.0000 6.750 1.2316 0.01440 0.00836 -0.0751 0.3584 1.0000 7.000 1.2482 0.01456 0.00852 -0.0732 0.3547 1.0000 7.250 1.2636 0.01477 0.00871 -0.0710 0.3511 1.0000 7.500 1.2791 0.01499 0.00893 -0.0689 0.3475 1.0000 7.750 1.2952 0.01511 0.00911 -0.0668 0.3435 1.0000 8.000 1.3103 0.01528 0.00930 -0.0646 0.3399 1.0000 8.250 1.3233 0.01549 0.00951 -0.0620 0.3360 1.0000 8.500 1.3344 0.01577 0.00977 -0.0591 0.3325 1.0000 8.750 1.3468 0.01598 0.01002 -0.0563 0.3295 1.0000 9.000 1.3553 0.01613 0.01024 -0.0528 0.3260 1.0000 9.250 1.3594 0.01632 0.01046 -0.0485 0.3222 1.0000 9.500 1.3633 0.01657 0.01072 -0.0443 0.3186 1.0000 9.750 1.3656 0.01694 0.01106 -0.0399 0.3148 1.0000 10.000 1.3735 0.01719 0.01139 -0.0365 0.3115 1.0000 10.250 1.3811 0.01748 0.01174 -0.0332 0.3078 1.0000 10.500 1.3860 0.01788 0.01215 -0.0296 0.3035 1.0000 10.750 1.3884 0.01841 0.01268 -0.0258 0.2993 1.0000 11.000 1.3951 0.01889 0.01320 -0.0227 0.2958 1.0000 11.250 1.4027 0.01936 0.01374 -0.0199 0.2915 1.0000 11.500 1.4068 0.02000 0.01439 -0.0168 0.2866 1.0000 11.750 1.4094 0.02078 0.01517 -0.0136 0.2825 1.0000 12.000 1.4166 0.02144 0.01589 -0.0111 0.2784 1.0000 12.250 1.4230 0.02218 0.01668 -0.0087 0.2737 1.0000 12.500 1.4266 0.02309 0.01761 -0.0060 0.2691 1.0000 12.750 1.4287 0.02415 0.01868 -0.0034 0.2643 1.0000 13.000 1.4357 0.02501 0.01961 -0.0014 0.2594 1.0000 13.250 1.4371 0.02623 0.02085 0.0010 0.2535 1.0000 13.500 1.4374 0.02760 0.02224 0.0033 0.2465 1.0000 13.750 1.4398 0.02891 0.02358 0.0053 0.2404 1.0000 14.000 1.4348 0.03078 0.02544 0.0077 0.2316 1.0000 14.250 1.4342 0.03244 0.02714 0.0095 0.2241 1.0000 14.500 1.4270 0.03468 0.02937 0.0116 0.2140 1.0000 14.750 1.4163 0.03732 0.03200 0.0135 0.2041 1.0000 15.000 1.4079 0.03992 0.03460 0.0152 0.1927 1.0000 15.250 1.3946 0.04306 0.03772 0.0167 0.1803 1.0000 15.500 1.3761 0.04681 0.04145 0.0182 0.1673 1.0000 15.750 1.3598 0.05054 0.04516 0.0193 0.1582 1.0000 16.000 1.3441 0.05432 0.04894 0.0202 0.1512 1.0000 16.250 1.3324 0.05780 0.05244 0.0209 0.1457 1.0000 16.500 1.3201 0.06145 0.05610 0.0215 0.1410 1.0000 16.750 1.3097 0.06496 0.05964 0.0219 0.1381 1.0000 17.000 1.3046 0.06797 0.06270 0.0222 0.1350 1.0000 17.250 1.2986 0.07110 0.06587 0.0224 0.1320 1.0000 17.500 1.2914 0.07441 0.06921 0.0226 0.1295 1.0000 17.750 1.2828 0.07792 0.07272 0.0226 0.1268 1.0000 18.000 1.2815 0.08057 0.07542 0.0227 0.1248 1.0000 18.250 1.2810 0.08324 0.07817 0.0227 0.1226 1.0000 18.500 1.2782 0.08618 0.08116 0.0226 0.1203 1.0000 18.750 1.2732 0.08939 0.08438 0.0224 0.1176 1.0000