XFOIL Version 6.96 Calculated polar for: GOE 491 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 ------ -------- --------- --------- -------- -------- -------- -8.250 -0.3656 0.07980 0.07767 -0.0120 1.0000 0.0071 -8.000 -0.3665 0.07607 0.07396 -0.0125 1.0000 0.0068 -7.500 -0.4590 0.08531 0.08314 -0.0080 1.0000 0.0070 -7.250 -0.4575 0.08202 0.07986 -0.0094 1.0000 0.0059 -7.000 -0.4533 0.07815 0.07600 -0.0117 1.0000 0.0059 -6.750 -0.4482 0.07345 0.07131 -0.0147 1.0000 0.0054 -6.500 -0.4415 0.06741 0.06525 -0.0183 1.0000 0.0050 -6.250 -0.4293 0.06582 0.06365 -0.0189 1.0000 0.0056 -6.000 -0.4167 0.06258 0.06038 -0.0204 1.0000 0.0062 -5.750 -0.4041 0.05825 0.05598 -0.0222 1.0000 0.0060 -5.500 -0.3895 0.05449 0.05216 -0.0234 1.0000 0.0064 -5.250 -0.3740 0.05022 0.04781 -0.0245 0.9999 0.0066 -5.000 -0.3401 0.04406 0.04146 -0.0297 0.9965 0.0063 -4.500 -0.2855 0.01870 0.01454 -0.0344 0.9835 0.0056 -4.000 -0.2309 0.01374 0.00866 -0.0342 0.9718 0.0064 -3.750 -0.2021 0.01241 0.00702 -0.0343 0.9649 0.0068 -3.500 -0.1725 0.01156 0.00598 -0.0345 0.9564 0.0075 -3.250 -0.1416 0.01057 0.00479 -0.0350 0.9478 0.0086 -3.000 -0.1047 0.00978 0.00383 -0.0369 0.9397 0.0099 -2.750 -0.0644 0.00919 0.00311 -0.0395 0.9290 0.0116 -2.500 -0.0243 0.00873 0.00252 -0.0421 0.9166 0.0146 -2.250 0.0118 0.00833 0.00208 -0.0437 0.9021 0.0249 -1.750 0.0729 0.00825 0.00192 -0.0447 0.8660 0.0472 -1.500 0.1007 0.00833 0.00194 -0.0445 0.8451 0.0536 -1.250 0.1268 0.00832 0.00182 -0.0439 0.8197 0.0563 -1.000 0.1512 0.00820 0.00156 -0.0430 0.7868 0.0586 -0.750 0.1752 0.00819 0.00140 -0.0420 0.7497 0.0607 -0.500 0.1989 0.00824 0.00127 -0.0409 0.7106 0.0629 0.000 0.2465 0.00840 0.00110 -0.0389 0.6336 0.0678 0.250 0.2702 0.00850 0.00104 -0.0380 0.5902 0.0719 0.500 0.2921 0.00877 0.00102 -0.0367 0.5149 0.0779 0.750 0.3152 0.00901 0.00103 -0.0358 0.4594 0.0854 1.000 0.3393 0.00915 0.00105 -0.0350 0.4254 0.1010 1.250 0.3642 0.00916 0.00108 -0.0344 0.4060 0.1357 1.500 0.3880 0.00896 0.00115 -0.0337 0.3916 0.2637 2.000 0.5190 0.00760 0.00143 -0.0514 0.3509 1.0000 2.250 0.5431 0.00775 0.00148 -0.0506 0.3290 1.0000 2.500 0.5669 0.00794 0.00156 -0.0497 0.3012 1.0000 2.750 0.5905 0.00816 0.00165 -0.0489 0.2715 1.0000 3.000 0.6140 0.00839 0.00176 -0.0480 0.2432 1.0000 3.500 0.6581 0.00924 0.00219 -0.0459 0.1503 1.0000 3.750 0.6805 0.00963 0.00242 -0.0449 0.1127 1.0000 4.000 0.7012 0.01025 0.00277 -0.0436 0.0540 1.0000 4.250 0.7243 0.01057 0.00305 -0.0427 0.0439 1.0000 4.500 0.7480 0.01082 0.00331 -0.0418 0.0396 1.0000 4.750 0.7718 0.01104 0.00357 -0.0410 0.0382 1.0000 5.000 0.7955 0.01128 0.00387 -0.0401 0.0377 1.0000 5.250 0.8190 0.01154 0.00421 -0.0393 0.0371 1.0000 5.500 0.8423 0.01184 0.00458 -0.0384 0.0355 1.0000 5.750 0.8647 0.01224 0.00502 -0.0374 0.0324 1.0000 6.000 0.8862 0.01275 0.00561 -0.0362 0.0291 1.0000 6.250 0.9104 0.01289 0.00579 -0.0356 0.0278 1.0000 6.500 0.9341 0.01310 0.00610 -0.0348 0.0239 1.0000 6.750 0.9568 0.01345 0.00644 -0.0339 0.0170 1.0000 7.000 0.9784 0.01393 0.00687 -0.0328 0.0108 1.0000 7.250 0.9995 0.01449 0.00752 -0.0316 0.0088 1.0000 7.500 1.0200 0.01511 0.00820 -0.0303 0.0076 1.0000 7.750 1.0389 0.01593 0.00913 -0.0287 0.0063 1.0000 8.000 1.0592 0.01654 0.00983 -0.0275 0.0056 1.0000 8.250 1.0782 0.01730 0.01070 -0.0260 0.0051 1.0000 8.500 1.0964 0.01813 0.01168 -0.0245 0.0046 1.0000 8.750 1.1111 0.01938 0.01308 -0.0225 0.0043 1.0000 9.000 1.1274 0.02042 0.01427 -0.0206 0.0041 1.0000 9.250 1.1426 0.02158 0.01560 -0.0187 0.0039 1.0000 9.500 1.1567 0.02285 0.01704 -0.0167 0.0037 1.0000 9.750 1.1696 0.02425 0.01864 -0.0146 0.0035 1.0000 10.000 1.1816 0.02571 0.02028 -0.0124 0.0033 1.0000 10.250 1.1950 0.02683 0.02154 -0.0106 0.0031 1.0000 10.500 1.2082 0.02782 0.02263 -0.0089 0.0029 1.0000 10.750 1.2151 0.02951 0.02451 -0.0064 0.0028 1.0000 11.000 1.2172 0.03149 0.02669 -0.0036 0.0026 1.0000 11.250 1.2132 0.03356 0.02900 0.0003 0.0025 1.0000 11.500 1.2082 0.03562 0.03127 0.0037 0.0025 1.0000 11.750 1.2019 0.03798 0.03385 0.0063 0.0025 1.0000 12.000 1.1910 0.04110 0.03722 0.0081 0.0024 1.0000 12.250 1.1800 0.04460 0.04091 0.0085 0.0025 1.0000 12.500 1.1664 0.04916 0.04570 0.0073 0.0024 1.0000 12.750 1.1539 0.05439 0.05112 0.0045 0.0025 1.0000 13.000 1.1367 0.06136 0.05830 0.0000 0.0024 1.0000 13.250 1.1204 0.06893 0.06606 -0.0051 0.0024 1.0000 13.500 1.1022 0.07685 0.07410 -0.0101 0.0024 1.0000 13.750 1.0816 0.08530 0.08266 -0.0151 0.0025 1.0000 14.000 1.0627 0.09380 0.09126 -0.0198 0.0025 1.0000 14.250 1.0451 0.10239 0.09995 -0.0244 0.0025 1.0000 14.500 1.0210 0.11229 0.10990 -0.0293 0.0026 1.0000