XFOIL Version 6.96 Calculated polar for: GOE 596 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.250 -0.3569 0.08977 0.08632 -0.0377 1.0000 0.0515 -8.000 -0.3756 0.08793 0.08458 -0.0380 1.0000 0.0517 -7.750 -0.3904 0.08560 0.08230 -0.0390 1.0000 0.0519 -7.500 -0.4044 0.08316 0.07986 -0.0393 1.0000 0.0520 -7.250 -0.4113 0.07911 0.07589 -0.0361 1.0000 0.0526 -7.000 -0.4124 0.07709 0.07394 -0.0316 1.0000 0.0532 -6.750 -0.3980 0.07476 0.07162 -0.0306 0.9980 0.0544 -6.500 -0.3697 0.07072 0.06754 -0.0361 0.9932 0.0566 -6.250 -0.3201 0.06290 0.05916 -0.0570 0.9834 0.0631 -6.000 -0.3022 0.05657 0.05286 -0.0599 0.9769 0.0644 -5.750 -0.2747 0.05375 0.05012 -0.0616 0.9728 0.0660 -5.500 -0.2457 0.05103 0.04735 -0.0645 0.9670 0.0693 -5.250 -0.2085 0.04512 0.04087 -0.0725 0.9592 0.0776 -5.000 -0.1758 0.04227 0.03810 -0.0753 0.9555 0.0798 -4.750 -0.1464 0.03991 0.03564 -0.0772 0.9472 0.0843 -4.500 -0.1069 0.03599 0.03131 -0.0820 0.9430 0.0934 -4.250 -0.0733 0.03522 0.03027 -0.0835 0.9347 0.1044 -4.000 -0.0426 0.03149 0.02656 -0.0860 0.9289 0.1101 -3.750 -0.0126 0.02964 0.02441 -0.0872 0.9196 0.1236 -3.500 0.0205 0.02801 0.02261 -0.0887 0.9119 0.1386 -3.250 0.0467 0.02665 0.02115 -0.0887 0.9000 0.1539 -3.000 0.0860 0.02106 0.01414 -0.0871 0.8907 0.0773 -2.750 0.1166 0.01931 0.01225 -0.0872 0.8798 0.0736 -2.500 0.1438 0.01770 0.01039 -0.0864 0.8657 0.0701 -2.250 0.1716 0.01653 0.00896 -0.0856 0.8510 0.0679 -2.000 0.1989 0.01566 0.00790 -0.0849 0.8357 0.0674 -1.750 0.2258 0.01495 0.00706 -0.0841 0.8196 0.0677 -1.500 0.2520 0.01442 0.00646 -0.0833 0.8026 0.0700 -1.250 0.2780 0.01394 0.00589 -0.0824 0.7855 0.0721 -1.000 0.3037 0.01348 0.00534 -0.0816 0.7690 0.0735 -0.750 0.3292 0.01312 0.00490 -0.0807 0.7535 0.0753 -0.500 0.3539 0.01267 0.00443 -0.0799 0.7388 0.0784 -0.250 0.3791 0.01240 0.00414 -0.0791 0.7249 0.0843 0.000 0.4046 0.01218 0.00389 -0.0784 0.7119 0.0951 0.250 0.4282 0.01155 0.00367 -0.0776 0.7004 0.2178 0.500 0.5030 0.00959 0.00357 -0.0870 0.6884 1.0000 0.750 0.5274 0.00973 0.00355 -0.0861 0.6773 1.0000 1.000 0.5517 0.00989 0.00359 -0.0853 0.6666 1.0000 1.250 0.5764 0.01006 0.00362 -0.0845 0.6572 1.0000 1.500 0.6009 0.01023 0.00369 -0.0837 0.6472 1.0000 1.750 0.6254 0.01042 0.00379 -0.0830 0.6375 1.0000 2.000 0.6506 0.01063 0.00388 -0.0823 0.6289 1.0000 2.250 0.6748 0.01081 0.00404 -0.0815 0.6194 1.0000 2.500 0.7000 0.01104 0.00417 -0.0808 0.6110 1.0000 2.750 0.7244 0.01123 0.00434 -0.0801 0.6012 1.0000 3.000 0.7490 0.01144 0.00451 -0.0793 0.5920 1.0000 3.250 0.7739 0.01165 0.00465 -0.0786 0.5825 1.0000 3.500 0.7978 0.01184 0.00485 -0.0777 0.5715 1.0000 3.750 0.8222 0.01204 0.00501 -0.0770 0.5611 1.0000 4.000 0.8468 0.01223 0.00515 -0.0762 0.5506 1.0000 4.250 0.8705 0.01240 0.00536 -0.0753 0.5390 1.0000 4.500 0.8945 0.01259 0.00553 -0.0744 0.5278 1.0000 4.750 0.9186 0.01277 0.00567 -0.0736 0.5163 1.0000 5.000 0.9420 0.01292 0.00580 -0.0726 0.5030 1.0000 5.250 0.9646 0.01304 0.00595 -0.0715 0.4884 1.0000 5.500 0.9874 0.01318 0.00611 -0.0704 0.4739 1.0000 5.750 1.0100 0.01333 0.00627 -0.0693 0.4587 1.0000 6.000 1.0324 0.01349 0.00645 -0.0682 0.4429 1.0000 6.250 1.0549 0.01369 0.00667 -0.0672 0.4276 1.0000 6.500 1.0768 0.01392 0.00689 -0.0660 0.4113 1.0000 6.750 1.0981 0.01416 0.00714 -0.0648 0.3927 1.0000 7.000 1.1188 0.01446 0.00745 -0.0635 0.3726 1.0000 7.250 1.1377 0.01485 0.00777 -0.0619 0.3492 1.0000 7.500 1.1561 0.01530 0.00817 -0.0603 0.3226 1.0000 7.750 1.1718 0.01588 0.00863 -0.0583 0.2851 1.0000 8.000 1.1811 0.01688 0.00929 -0.0555 0.2140 1.0000 8.250 1.1792 0.01881 0.01056 -0.0513 0.1219 1.0000 8.500 1.1816 0.02043 0.01181 -0.0477 0.0829 1.0000 8.750 1.1894 0.02150 0.01287 -0.0447 0.0741 1.0000 9.000 1.1933 0.02264 0.01402 -0.0411 0.0691 1.0000 9.250 1.2005 0.02364 0.01511 -0.0382 0.0656 1.0000 9.500 1.2047 0.02485 0.01639 -0.0351 0.0625 1.0000 9.750 1.2041 0.02646 0.01799 -0.0318 0.0599 1.0000 10.000 1.2088 0.02786 0.01947 -0.0292 0.0579 1.0000 10.250 1.2160 0.02919 0.02089 -0.0271 0.0558 1.0000 10.500 1.2226 0.03065 0.02241 -0.0252 0.0538 1.0000 10.750 1.2290 0.03225 0.02403 -0.0233 0.0518 1.0000 11.000 1.2370 0.03425 0.02598 -0.0216 0.0495 1.0000 11.250 1.2494 0.03574 0.02757 -0.0202 0.0479 1.0000 11.500 1.2631 0.03716 0.02909 -0.0190 0.0464 1.0000 11.750 1.2768 0.03867 0.03069 -0.0178 0.0446 1.0000 12.000 1.2889 0.04024 0.03230 -0.0167 0.0428 1.0000 12.250 1.3260 0.04288 0.03485 -0.0173 0.0401 1.0000 12.500 1.3320 0.04454 0.03674 -0.0157 0.0395 1.0000 12.750 1.3390 0.04647 0.03889 -0.0142 0.0386 1.0000 13.000 1.3455 0.04859 0.04122 -0.0130 0.0377 1.0000 13.250 1.3505 0.05083 0.04365 -0.0118 0.0366 1.0000 13.500 1.3558 0.05302 0.04598 -0.0108 0.0355 1.0000 13.750 1.3625 0.05526 0.04831 -0.0100 0.0345 1.0000 14.000 1.3693 0.05805 0.05122 -0.0094 0.0338 1.0000 14.250 1.3804 0.06231 0.05563 -0.0090 0.0330 1.0000 14.750 1.3603 0.07102 0.06484 -0.0078 0.0327 1.0000 15.000 1.3436 0.07498 0.06905 -0.0078 0.0326 1.0000 15.250 1.3272 0.07952 0.07382 -0.0083 0.0326 1.0000 15.500 1.3074 0.08435 0.07888 -0.0095 0.0325 1.0000 15.750 1.2902 0.08986 0.08460 -0.0111 0.0326 1.0000 16.000 1.2700 0.09575 0.09070 -0.0134 0.0326 1.0000 16.250 1.2484 0.10197 0.09713 -0.0163 0.0326 1.0000 16.500 1.2301 0.10897 0.10430 -0.0193 0.0327 1.0000 17.000 1.0727 0.14979 0.14606 -0.0495 0.0378 1.0000 17.250 1.0423 0.16398 0.16029 -0.0577 0.0395 1.0000