XFOIL Version 6.96 Calculated polar for: GOE 679 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.250 -0.4433 0.19246 0.18959 -0.0248 1.0000 0.0237 -18.750 -0.7019 0.12506 0.12149 -0.0566 1.0000 0.0300 -18.500 -0.7294 0.11682 0.11309 -0.0607 1.0000 0.0301 -18.250 -0.7512 0.10983 0.10596 -0.0642 1.0000 0.0303 -18.000 -0.7658 0.10430 0.10034 -0.0667 1.0000 0.0303 -17.750 -0.7788 0.09917 0.09512 -0.0690 1.0000 0.0304 -17.500 -0.7906 0.09437 0.09023 -0.0710 1.0000 0.0305 -17.250 -0.8009 0.08993 0.08571 -0.0728 1.0000 0.0306 -17.000 -0.8056 0.08546 0.08117 -0.0756 0.9996 0.0306 -16.750 -0.8063 0.08085 0.07649 -0.0795 0.9986 0.0308 -16.500 -0.8049 0.07678 0.07237 -0.0829 0.9975 0.0310 -16.250 -0.8071 0.07241 0.06795 -0.0865 0.9962 0.0310 -16.000 -0.8099 0.06798 0.06345 -0.0902 0.9949 0.0312 -15.750 -0.8150 0.06339 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0.4671 0.2237 -0.250 0.3363 0.01125 0.00334 -0.0702 0.4587 0.2314 0.000 0.3564 0.01131 0.00340 -0.0685 0.4496 0.2409 0.250 0.3772 0.01140 0.00345 -0.0669 0.4414 0.2493 0.500 0.3984 0.01144 0.00351 -0.0655 0.4336 0.2598 0.750 0.4182 0.01155 0.00358 -0.0637 0.4259 0.2704 1.000 0.4402 0.01157 0.00364 -0.0625 0.4200 0.2824 1.250 0.4618 0.01164 0.00371 -0.0611 0.4137 0.2929 1.500 0.4815 0.01173 0.00380 -0.0594 0.4074 0.3062 1.750 0.5029 0.01178 0.00388 -0.0580 0.4024 0.3197 2.250 0.5442 0.01189 0.00406 -0.0550 0.3913 0.3542 2.750 0.5842 0.01195 0.00428 -0.0518 0.3812 0.4125 3.000 0.6033 0.01195 0.00440 -0.0500 0.3758 0.4562 3.250 0.6199 0.01195 0.00455 -0.0478 0.3705 0.5141 3.500 0.6343 0.01183 0.00471 -0.0451 0.3661 0.6055 3.750 0.6464 0.01161 0.00487 -0.0418 0.3615 0.7197 4.250 0.8537 0.01205 0.00578 -0.0742 0.3415 0.9842 4.500 0.8855 0.01242 0.00609 -0.0752 0.3350 0.9990 4.750 0.9085 0.01265 0.00627 -0.0745 0.3291 1.0000 5.000 0.9259 0.01282 0.00641 -0.0724 0.3235 1.0000 5.250 0.9415 0.01305 0.00660 -0.0701 0.3173 1.0000 5.500 0.9580 0.01328 0.00679 -0.0680 0.3123 1.0000 5.750 0.9763 0.01348 0.00698 -0.0663 0.3068 1.0000 6.000 0.9933 0.01374 0.00720 -0.0643 0.3009 1.0000 6.250 1.0096 0.01403 0.00745 -0.0623 0.2955 1.0000 6.500 1.0280 0.01428 0.00769 -0.0607 0.2900 1.0000 6.750 1.0450 0.01459 0.00797 -0.0588 0.2837 1.0000 7.000 1.0616 0.01493 0.00827 -0.0570 0.2780 1.0000 7.250 1.0794 0.01525 0.00857 -0.0554 0.2722 1.0000 7.500 1.0955 0.01564 0.00893 -0.0535 0.2661 1.0000 7.750 1.1123 0.01602 0.00929 -0.0519 0.2608 1.0000 8.000 1.1293 0.01641 0.00966 -0.0503 0.2548 1.0000 8.250 1.1444 0.01689 0.01010 -0.0484 0.2489 1.0000 8.500 1.1611 0.01732 0.01053 -0.0469 0.2438 1.0000 8.750 1.1773 0.01778 0.01098 -0.0453 0.2383 1.0000 9.000 1.1925 0.01831 0.01149 -0.0436 0.2337 1.0000 9.250 1.2078 0.01885 0.01202 -0.0420 0.2300 1.0000 9.500 1.2249 0.01933 0.01251 -0.0407 0.2264 1.0000 9.750 1.2403 0.01990 0.01308 -0.0393 0.2220 1.0000 10.000 1.2534 0.02060 0.01376 -0.0376 0.2175 1.0000 10.250 1.2684 0.02123 0.01440 -0.0362 0.2144 1.0000 10.500 1.2844 0.02183 0.01502 -0.0349 0.2114 1.0000 10.750 1.2995 0.02249 0.01570 -0.0337 0.2081 1.0000 11.000 1.3132 0.02325 0.01647 -0.0323 0.2053 1.0000 11.250 1.3253 0.02412 0.01734 -0.0309 0.2022 1.0000 11.500 1.3387 0.02494 0.01818 -0.0296 0.1996 1.0000 11.750 1.3538 0.02568 0.01896 -0.0286 0.1972 1.0000 12.000 1.3674 0.02653 0.01985 -0.0275 0.1946 1.0000 12.250 1.3805 0.02744 0.02078 -0.0263 0.1923 1.0000 12.500 1.3919 0.02848 0.02184 -0.0252 0.1899 1.0000 12.750 1.4019 0.02963 0.02301 -0.0240 0.1873 1.0000 13.000 1.4133 0.03072 0.02413 -0.0229 0.1852 1.0000 13.250 1.4266 0.03169 0.02516 -0.0221 0.1834 1.0000 13.500 1.4381 0.03281 0.02632 -0.0211 0.1807 1.0000 13.750 1.4490 0.03401 0.02756 -0.0202 0.1786 1.0000 14.000 1.4574 0.03541 0.02899 -0.0193 0.1762 1.0000 14.250 1.4652 0.03688 0.03049 -0.0183 0.1741 1.0000 14.500 1.4724 0.03844 0.03208 -0.0175 0.1719 1.0000 14.750 1.4831 0.03974 0.03345 -0.0168 0.1701 1.0000 15.000 1.4927 0.04115 0.03492 -0.0162 0.1682 1.0000 15.250 1.5002 0.04278 0.03660 -0.0155 0.1656 1.0000 15.500 1.5065 0.04452 0.03839 -0.0149 0.1635 1.0000 15.750 1.5099 0.04659 0.04049 -0.0142 0.1611 1.0000 16.000 1.5129 0.04872 0.04266 -0.0137 0.1591 1.0000 16.250 1.5206 0.05044 0.04446 -0.0133 0.1575 1.0000 16.500 1.5270 0.05233 0.04641 -0.0130 0.1556 1.0000 16.750 1.5320 0.05436 0.04851 -0.0127 0.1534 1.0000 17.000 1.5336 0.05678 0.05099 -0.0124 0.1510 1.0000 17.250 1.5327 0.05951 0.05376 -0.0123 0.1485 1.0000 17.500 1.5323 0.06222 0.05652 -0.0122 0.1463 1.0000 17.750 1.5361 0.06452 0.05890 -0.0122 0.1441 1.0000 18.000 1.5360 0.06728 0.06173 -0.0122 0.1407 1.0000 18.250 1.5331 0.07037 0.06487 -0.0124 0.1377 1.0000 18.500 1.5262 0.07398 0.06853 -0.0127 0.1348 1.0000 18.750 1.5258 0.07687 0.07150 -0.0130 0.1317 1.0000 19.000 1.5191 0.08055 0.07522 -0.0135 0.1270 1.0000 19.250 1.5106 0.08446 0.07918 -0.0141 0.1242 1.0000