XFOIL Version 6.96 Calculated polar for: GOE 13K 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 ------ -------- --------- --------- -------- -------- -------- -14.500 -0.0399 0.12273 0.12051 -0.1570 0.9523 0.0305 -14.250 -0.0248 0.11881 0.11657 -0.1613 0.9537 0.0310 -13.750 -0.5047 0.03229 0.02908 -0.2065 0.9345 0.0385 -13.500 -0.4918 0.03103 0.02776 -0.2070 0.9329 0.0388 -13.250 -0.4679 0.03041 0.02712 -0.2082 0.9319 0.0390 -13.000 -0.4403 0.02994 0.02664 -0.2097 0.9311 0.0393 -12.750 -0.4326 0.02936 0.02601 -0.2077 0.9272 0.0395 -12.500 -0.4282 0.02855 0.02511 -0.2051 0.9230 0.0397 -12.250 -0.4049 0.02824 0.02479 -0.2054 0.9211 0.0400 -12.000 -0.3924 0.02674 0.02312 -0.2050 0.9188 0.0404 -11.750 -0.3691 0.02573 0.02198 -0.2061 0.9170 0.0409 -11.500 -0.3880 0.02504 0.02119 -0.1976 0.9103 0.0410 -11.250 -0.3747 0.02417 0.02018 -0.1960 0.9074 0.0416 -11.000 -0.3560 0.02278 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0.00933 0.00330 -0.1286 0.8077 0.0602 -1.250 0.3454 0.00933 0.00331 -0.1237 0.8042 0.0606 -1.000 0.3629 0.00928 0.00325 -0.1214 0.8013 0.0617 -0.750 0.3839 0.00921 0.00318 -0.1199 0.7986 0.0624 -0.500 0.4113 0.00912 0.00308 -0.1199 0.7968 0.0632 -0.250 0.4428 0.00897 0.00293 -0.1208 0.7949 0.0663 0.000 0.4680 0.00892 0.00290 -0.1203 0.7927 0.0684 0.250 0.4761 0.00896 0.00297 -0.1160 0.7896 0.0698 0.500 0.4913 0.00896 0.00298 -0.1132 0.7866 0.0738 0.750 0.5117 0.00891 0.00298 -0.1116 0.7840 0.0803 1.000 0.5368 0.00875 0.00300 -0.1112 0.7819 0.1290 1.250 0.5680 0.00863 0.00297 -0.1121 0.7798 0.1647 1.500 0.6043 0.00847 0.00295 -0.1142 0.7775 0.2082 1.750 0.6174 0.00830 0.00314 -0.1113 0.7747 0.3306 2.000 0.8606 0.00743 0.00408 -0.1617 0.7784 0.9774 2.250 0.9257 0.00774 0.00439 -0.1702 0.7765 0.9887 2.500 0.9712 0.00791 0.00459 -0.1744 0.7726 0.9949 2.750 1.0178 0.00789 0.00450 -0.1788 0.7625 0.9996 3.000 1.0242 0.00802 0.00465 -0.1742 0.7551 1.0000 3.250 1.0344 0.00813 0.00470 -0.1703 0.7453 1.0000 3.500 1.0358 0.00835 0.00490 -0.1646 0.7342 1.0000 3.750 1.0441 0.00854 0.00507 -0.1604 0.7231 1.0000 4.000 1.0509 0.00878 0.00526 -0.1559 0.7105 1.0000 4.250 1.0573 0.00906 0.00549 -0.1513 0.6972 1.0000 4.500 1.0642 0.00938 0.00576 -0.1470 0.6811 1.0000 4.750 1.0633 0.00987 0.00618 -0.1410 0.6547 1.0000 5.000 1.0161 0.01162 0.00752 -0.1256 0.5668 1.0000 5.250 0.9748 0.01370 0.00917 -0.1122 0.4845 1.0000 5.500 0.9737 0.01465 0.00997 -0.1070 0.4534 1.0000 5.750 0.9825 0.01529 0.01054 -0.1036 0.4363 1.0000 6.000 0.9937 0.01586 0.01104 -0.1007 0.4222 1.0000 6.250 1.0062 0.01640 0.01155 -0.0981 0.4110 1.0000 6.500 1.0203 0.01690 0.01202 -0.0959 0.3995 1.0000 6.750 1.0334 0.01744 0.01251 -0.0935 0.3888 1.0000 7.000 1.0503 0.01785 0.01291 -0.0917 0.3785 1.0000 7.250 1.0638 0.01841 0.01344 -0.0895 0.3669 1.0000 7.500 1.0771 0.01899 0.01395 -0.0872 0.3529 1.0000 7.750 1.0907 0.01956 0.01446 -0.0850 0.3353 1.0000 8.000 1.1026 0.02023 0.01505 -0.0826 0.3132 1.0000 8.250 1.1093 0.02115 0.01580 -0.0794 0.2798 1.0000 8.500 1.1119 0.02229 0.01668 -0.0756 0.2343 1.0000 8.750 1.1183 0.02327 0.01748 -0.0725 0.2005 1.0000 9.000 1.1259 0.02422 0.01825 -0.0697 0.1688 1.0000 9.250 1.1359 0.02507 0.01895 -0.0672 0.1428 1.0000 9.500 1.1485 0.02581 0.01958 -0.0652 0.1258 1.0000 9.750 1.1622 0.02650 0.02022 -0.0634 0.1141 1.0000 10.000 1.1759 0.02720 0.02086 -0.0616 0.1039 1.0000 10.250 1.1912 0.02782 0.02146 -0.0600 0.0972 1.0000 10.500 1.2058 0.02848 0.02208 -0.0584 0.0906 1.0000 10.750 1.2214 0.02909 0.02269 -0.0570 0.0856 1.0000 11.000 1.2355 0.02979 0.02337 -0.0554 0.0808 1.0000 11.250 1.2496 0.03051 0.02408 -0.0538 0.0770 1.0000 11.500 1.2656 0.03112 0.02472 -0.0525 0.0747 1.0000 11.750 1.2804 0.03181 0.02540 -0.0510 0.0715 1.0000 12.000 1.2936 0.03261 0.02618 -0.0494 0.0677 1.0000 12.250 1.3085 0.03330 0.02691 -0.0481 0.0666 1.0000 12.500 1.3229 0.03402 0.02765 -0.0467 0.0644 1.0000 12.750 1.3366 0.03480 0.02843 -0.0452 0.0619 1.0000 13.000 1.3487 0.03570 0.02932 -0.0436 0.0594 1.0000 13.250 1.3636 0.03641 0.03008 -0.0424 0.0580 1.0000 13.500 1.3770 0.03724 0.03093 -0.0410 0.0563 1.0000 13.750 1.3895 0.03813 0.03184 -0.0396 0.0545 1.0000 14.000 1.3996 0.03920 0.03290 -0.0379 0.0519 1.0000 14.250 1.4139 0.03998 0.03374 -0.0367 0.0506 1.0000 14.500 1.4264 0.04090 0.03470 -0.0354 0.0491 1.0000 14.750 1.4376 0.04190 0.03570 -0.0340 0.0470 1.0000 15.000 1.4468 0.04308 0.03689 -0.0323 0.0451 1.0000 15.250 1.4593 0.04403 0.03789 -0.0311 0.0437 1.0000 15.500 1.4703 0.04509 0.03897 -0.0298 0.0418 1.0000 15.750 1.4782 0.04640 0.04029 -0.0282 0.0398 1.0000 16.000 1.4879 0.04760 0.04155 -0.0269 0.0386 1.0000 16.250 1.4976 0.04880 0.04277 -0.0256 0.0365 1.0000 16.500 1.5051 0.05019 0.04418 -0.0241 0.0351 1.0000 16.750 1.5115 0.05170 0.04573 -0.0227 0.0339 1.0000 17.000 1.5201 0.05304 0.04712 -0.0214 0.0326 1.0000 17.250 1.5260 0.05462 0.04874 -0.0200 0.0313 1.0000 17.500 1.5287 0.05652 0.05066 -0.0185 0.0299 1.0000 17.750 1.5355 0.05808 0.05228 -0.0173 0.0290 1.0000 18.000 1.5397 0.05991 0.05418 -0.0161 0.0284 1.0000 18.250 1.5437 0.06178 0.05608 -0.0149 0.0270 1.0000 18.500 1.5452 0.06391 0.05826 -0.0137 0.0263 1.0000 18.750 1.5453 0.06623 0.06064 -0.0125 0.0254 1.0000 19.000 1.5487 0.06825 0.06274 -0.0115 0.0248 1.0000 19.250 1.5499 0.07055 0.06511 -0.0106 0.0242 1.0000