XFOIL Version 6.96 Calculated polar for: GOE 566 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 ------ -------- --------- --------- -------- -------- -------- -9.000 -0.4534 0.08225 0.07997 -0.0361 1.0000 0.0257 -8.750 -0.4732 0.07565 0.07343 -0.0389 1.0000 0.0260 -8.500 -0.4845 0.07181 0.06962 -0.0404 1.0000 0.0262 -8.250 -0.4878 0.06825 0.06607 -0.0415 1.0000 0.0264 -8.000 -0.4860 0.06653 0.06436 -0.0404 1.0000 0.0268 -7.750 -0.4930 0.06336 0.06118 -0.0399 1.0000 0.0270 -7.500 -0.5026 0.06144 0.05926 -0.0371 1.0000 0.0273 -7.250 -0.4879 0.05755 0.05529 -0.0404 0.9975 0.0281 -7.000 -0.4554 0.04896 0.04624 -0.0492 0.9920 0.0325 -6.750 -0.4349 0.04250 0.03935 -0.0530 0.9867 0.0326 -6.250 -0.3996 0.02873 0.02480 -0.0577 0.9767 0.0342 -6.000 -0.3706 0.02590 0.02172 -0.0592 0.9736 0.0348 -5.750 -0.3378 0.02449 0.02019 -0.0610 0.9717 0.0364 -5.500 -0.3137 0.01862 0.01328 -0.0604 0.9669 0.0337 -5.250 -0.2842 0.01754 0.01215 -0.0612 0.9624 0.0352 -5.000 -0.2519 0.01641 0.01088 -0.0623 0.9591 0.0362 -4.750 -0.2191 0.01527 0.00958 -0.0633 0.9561 0.0372 -4.500 -0.1923 0.01453 0.00873 -0.0630 0.9495 0.0384 -4.250 -0.1625 0.01378 0.00786 -0.0633 0.9444 0.0395 -4.000 -0.1332 0.01304 0.00702 -0.0634 0.9393 0.0401 -3.750 -0.1072 0.01246 0.00637 -0.0628 0.9319 0.0407 -3.500 -0.0787 0.01209 0.00592 -0.0627 0.9264 0.0414 -3.250 -0.0554 0.01108 0.00485 -0.0617 0.9179 0.0428 -3.000 -0.0298 0.01047 0.00419 -0.0610 0.9106 0.0440 -2.750 -0.0059 0.01007 0.00377 -0.0600 0.9005 0.0451 -2.500 0.0191 0.00974 0.00340 -0.0592 0.8910 0.0465 -2.250 0.0444 0.00945 0.00306 -0.0584 0.8811 0.0480 -2.000 0.0693 0.00921 0.00279 -0.0575 0.8696 0.0500 -1.750 0.0950 0.00903 0.00255 -0.0568 0.8588 0.0522 -1.500 0.1203 0.00874 0.00221 -0.0560 0.8482 0.0566 -1.250 0.1461 0.00854 0.00200 -0.0553 0.8370 0.0635 -1.000 0.1700 0.00807 0.00184 -0.0545 0.8246 0.1509 -0.750 0.1922 0.00740 0.00171 -0.0535 0.8124 0.3246 -0.500 0.2067 0.00624 0.00169 -0.0510 0.8019 0.6810 -0.250 0.2256 0.00576 0.00172 -0.0485 0.7916 0.8387 0.000 0.2825 0.00564 0.00180 -0.0542 0.7812 0.9503 0.250 0.3330 0.00573 0.00182 -0.0588 0.7697 0.9779 0.500 0.3877 0.00584 0.00181 -0.0644 0.7523 0.9946 1.000 0.4508 0.00593 0.00168 -0.0659 0.7121 1.0000 1.250 0.4735 0.00600 0.00165 -0.0648 0.6920 1.0000 1.500 0.4963 0.00609 0.00165 -0.0636 0.6728 1.0000 1.750 0.5194 0.00619 0.00166 -0.0626 0.6527 1.0000 2.000 0.5424 0.00631 0.00169 -0.0615 0.6304 1.0000 2.250 0.5652 0.00646 0.00174 -0.0604 0.6054 1.0000 2.500 0.5876 0.00664 0.00180 -0.0592 0.5737 1.0000 2.750 0.6091 0.00689 0.00187 -0.0578 0.5287 1.0000 3.000 0.6287 0.00729 0.00199 -0.0562 0.4667 1.0000 3.250 0.6483 0.00776 0.00218 -0.0546 0.4104 1.0000 3.500 0.6693 0.00815 0.00238 -0.0533 0.3676 1.0000 3.750 0.6910 0.00851 0.00257 -0.0522 0.3325 1.0000 4.000 0.7129 0.00885 0.00277 -0.0511 0.3026 1.0000 4.250 0.7353 0.00917 0.00298 -0.0500 0.2791 1.0000 4.500 0.7584 0.00944 0.00318 -0.0491 0.2643 1.0000 4.750 0.7817 0.00969 0.00339 -0.0482 0.2540 1.0000 5.250 0.8286 0.01016 0.00382 -0.0466 0.2324 1.0000 5.500 0.8522 0.01039 0.00404 -0.0458 0.2236 1.0000 5.750 0.8753 0.01066 0.00427 -0.0449 0.2117 1.0000 6.000 0.8988 0.01091 0.00450 -0.0441 0.1981 1.0000 6.250 0.9224 0.01116 0.00473 -0.0433 0.1827 1.0000 6.500 0.9452 0.01147 0.00496 -0.0425 0.1567 1.0000 6.750 0.9645 0.01211 0.00534 -0.0412 0.1125 1.0000 7.000 0.9839 0.01276 0.00586 -0.0398 0.0900 1.0000 7.250 1.0048 0.01328 0.00634 -0.0387 0.0750 1.0000 7.500 1.0243 0.01394 0.00684 -0.0373 0.0488 1.0000 7.750 1.0435 0.01463 0.00746 -0.0359 0.0385 1.0000 8.000 1.0628 0.01530 0.00816 -0.0345 0.0338 1.0000 8.250 1.0824 0.01593 0.00886 -0.0332 0.0311 1.0000 8.500 1.0981 0.01688 0.00986 -0.0313 0.0281 1.0000 8.750 1.1154 0.01764 0.01071 -0.0296 0.0264 1.0000 9.000 1.1340 0.01826 0.01139 -0.0282 0.0247 1.0000 9.250 1.1509 0.01898 0.01217 -0.0266 0.0231 1.0000 9.500 1.1623 0.02011 0.01334 -0.0242 0.0217 1.0000 9.750 1.1717 0.02140 0.01473 -0.0215 0.0208 1.0000 10.000 1.1872 0.02207 0.01550 -0.0197 0.0201 1.0000 10.250 1.2000 0.02281 0.01631 -0.0174 0.0191 1.0000 10.500 1.2110 0.02365 0.01722 -0.0150 0.0184 1.0000 10.750 1.2220 0.02446 0.01809 -0.0127 0.0176 1.0000 11.000 1.2302 0.02553 0.01920 -0.0103 0.0169 1.0000 11.250 1.2291 0.02786 0.02162 -0.0071 0.0162 1.0000 11.500 1.2398 0.02876 0.02263 -0.0052 0.0159 1.0000 11.750 1.2486 0.02995 0.02395 -0.0033 0.0154 1.0000 12.000 1.2557 0.03138 0.02551 -0.0013 0.0151 1.0000 12.250 1.2619 0.03294 0.02719 0.0005 0.0147 1.0000 12.500 1.2670 0.03461 0.02898 0.0022 0.0143 1.0000 12.750 1.2715 0.03630 0.03080 0.0037 0.0140 1.0000 13.000 1.2745 0.03821 0.03282 0.0051 0.0137 1.0000 13.250 1.2772 0.04011 0.03481 0.0062 0.0133 1.0000 13.500 1.2786 0.04226 0.03706 0.0071 0.0131 1.0000 13.750 1.2782 0.04468 0.03952 0.0077 0.0126 1.0000 14.000 1.2708 0.04842 0.04344 0.0085 0.0125 1.0000 14.250 1.2595 0.05275 0.04798 0.0089 0.0123 1.0000 14.500 1.2548 0.05576 0.05116 0.0083 0.0122 1.0000 14.750 1.2464 0.05971 0.05531 0.0073 0.0120 1.0000 15.000 1.2349 0.06441 0.06019 0.0060 0.0120 1.0000 15.250 1.2256 0.06899 0.06494 0.0040 0.0118 1.0000 15.500 1.2099 0.07497 0.07111 0.0014 0.0118 1.0000 15.750 1.1942 0.08135 0.07766 -0.0018 0.0118 1.0000 16.000 1.1771 0.08848 0.08498 -0.0059 0.0117 1.0000 16.250 1.1596 0.09590 0.09256 -0.0100 0.0118 1.0000 16.500 1.1393 0.10441 0.10123 -0.0152 0.0118 1.0000 16.750 1.1179 0.11354 0.11052 -0.0207 0.0119 1.0000 17.000 1.0970 0.12278 0.11991 -0.0263 0.0120 1.0000 17.250 1.0722 0.13342 0.13068 -0.0328 0.0121 1.0000 17.500 1.0435 0.14557 0.14297 -0.0401 0.0123 1.0000