XFOIL Version 6.96 Calculated polar for: GOE 628 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -0.7381 0.12462 0.12230 -0.0545 1.0000 0.0277 -19.500 -0.7865 0.11257 0.11009 -0.0618 1.0000 0.0291 -19.250 -0.8111 0.10497 0.10238 -0.0664 1.0000 0.0300 -19.000 -0.8235 0.09945 0.09685 -0.0697 1.0000 0.0307 -18.750 -0.8330 0.09450 0.09185 -0.0725 1.0000 0.0313 -18.500 -0.8441 0.08936 0.08665 -0.0755 1.0000 0.0320 -18.250 -0.8572 0.08401 0.08121 -0.0787 1.0000 0.0327 -18.000 -0.8703 0.07882 0.07593 -0.0818 1.0000 0.0332 -17.750 -0.8818 0.07389 0.07089 -0.0847 1.0000 0.0337 -17.500 -0.8882 0.06998 0.06698 -0.0868 1.0000 0.0343 -17.250 -0.8972 0.06580 0.06276 -0.0891 1.0000 0.0346 -17.000 -0.9041 0.06201 0.05893 -0.0911 1.0000 0.0349 -16.750 -0.9098 0.05848 0.05537 -0.0930 1.0000 0.0354 -16.500 -0.9212 0.05466 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3.000 0.8811 0.00979 0.00320 -0.0996 0.3527 0.3861 3.250 0.9041 0.00994 0.00334 -0.0986 0.3453 0.3954 3.500 0.9285 0.01005 0.00345 -0.0978 0.3399 0.4045 3.750 0.9521 0.01016 0.00358 -0.0969 0.3343 0.4150 4.250 0.9977 0.01043 0.00387 -0.0948 0.3241 0.4384 4.500 1.0211 0.01051 0.00400 -0.0939 0.3204 0.4547 4.750 1.0423 0.01062 0.00415 -0.0926 0.3165 0.4753 5.000 1.0611 0.01073 0.00431 -0.0908 0.3123 0.5039 5.250 1.0785 0.01077 0.00451 -0.0888 0.3085 0.5695 5.500 1.1488 0.01032 0.00497 -0.0980 0.3044 1.0000 5.750 1.1687 0.01049 0.00512 -0.0964 0.3013 1.0000 6.000 1.1874 0.01069 0.00529 -0.0946 0.2981 1.0000 6.250 1.2051 0.01093 0.00550 -0.0927 0.2945 1.0000 6.500 1.2235 0.01117 0.00573 -0.0909 0.2915 1.0000 6.750 1.2454 0.01131 0.00589 -0.0898 0.2897 1.0000 7.000 1.2668 0.01148 0.00607 -0.0886 0.2873 1.0000 7.250 1.2871 0.01169 0.00628 -0.0873 0.2846 1.0000 7.500 1.3066 0.01194 0.00651 -0.0858 0.2818 1.0000 7.750 1.3248 0.01224 0.00680 -0.0842 0.2786 1.0000 8.000 1.3421 0.01259 0.00714 -0.0825 0.2751 1.0000 8.250 1.3651 0.01274 0.00732 -0.0818 0.2727 1.0000 8.500 1.3863 0.01296 0.00755 -0.0808 0.2698 1.0000 8.750 1.4060 0.01324 0.00783 -0.0795 0.2666 1.0000 9.000 1.4247 0.01358 0.00817 -0.0782 0.2640 1.0000 9.250 1.4414 0.01401 0.00859 -0.0767 0.2608 1.0000 9.500 1.4601 0.01438 0.00897 -0.0754 0.2585 1.0000 9.750 1.4812 0.01464 0.00928 -0.0746 0.2566 1.0000 10.000 1.5015 0.01496 0.00962 -0.0736 0.2545 1.0000 10.250 1.5208 0.01533 0.01001 -0.0726 0.2519 1.0000 10.500 1.5386 0.01578 0.01047 -0.0715 0.2492 1.0000 10.750 1.5551 0.01631 0.01100 -0.0702 0.2463 1.0000 11.000 1.5696 0.01696 0.01166 -0.0687 0.2432 1.0000 11.250 1.5902 0.01732 0.01207 -0.0680 0.2416 1.0000 11.500 1.6096 0.01775 0.01254 -0.0672 0.2393 1.0000 11.750 1.6273 0.01827 0.01309 -0.0663 0.2366 1.0000 12.000 1.6435 0.01889 0.01373 -0.0653 0.2337 1.0000 12.250 1.6565 0.01973 0.01455 -0.0640 0.2298 1.0000 12.500 1.6732 0.02036 0.01523 -0.0631 0.2263 1.0000 12.750 1.6907 0.02095 0.01585 -0.0623 0.2222 1.0000 13.000 1.7044 0.02180 0.01671 -0.0613 0.2181 1.0000 13.250 1.7143 0.02292 0.01782 -0.0600 0.2136 1.0000 13.500 1.7306 0.02365 0.01860 -0.0593 0.2107 1.0000 13.750 1.7448 0.02453 0.01952 -0.0584 0.2069 1.0000 14.000 1.7539 0.02579 0.02077 -0.0573 0.2015 1.0000 14.250 1.7639 0.02702 0.02204 -0.0563 0.1979 1.0000 14.500 1.7767 0.02807 0.02313 -0.0556 0.1939 1.0000 14.750 1.7850 0.02950 0.02457 -0.0546 0.1889 1.0000 15.000 1.7905 0.03117 0.02625 -0.0536 0.1836 1.0000 15.250 1.7996 0.03258 0.02770 -0.0528 0.1792 1.0000 15.500 1.8010 0.03467 0.02978 -0.0518 0.1726 1.0000 15.750 1.8070 0.03640 0.03154 -0.0510 0.1675 1.0000 16.000 1.8081 0.03858 0.03374 -0.0501 0.1616 1.0000 16.250 1.8081 0.04092 0.03610 -0.0493 0.1561 1.0000 16.500 1.8097 0.04315 0.03836 -0.0486 0.1511 1.0000 16.750 1.8041 0.04612 0.04133 -0.0478 0.1448 1.0000 17.000 1.8037 0.04861 0.04386 -0.0473 0.1399 1.0000 17.250 1.7952 0.05200 0.04727 -0.0467 0.1343 1.0000 17.500 1.7903 0.05512 0.05042 -0.0463 0.1290 1.0000 17.750 1.7810 0.05872 0.05405 -0.0460 0.1242 1.0000 18.000 1.7734 0.06222 0.05761 -0.0458 0.1207 1.0000 18.250 1.7682 0.06552 0.06095 -0.0457 0.1170 1.0000 18.500 1.7558 0.06968 0.06515 -0.0457 0.1130 1.0000 18.750 1.7451 0.07370 0.06924 -0.0458 0.1099 1.0000 19.000 1.7365 0.07755 0.07315 -0.0461 0.1068 1.0000 19.250 1.7224 0.08211 0.07777 -0.0465 0.1034 1.0000