XFOIL Version 6.96 Calculated polar for: GOE 284 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 ------ -------- --------- --------- -------- -------- -------- -16.000 -0.8685 0.07092 0.06736 -0.0682 1.0000 0.0381 -15.750 -0.9127 0.06002 0.05624 -0.0766 1.0000 0.0380 -15.500 -0.9395 0.05135 0.04737 -0.0841 1.0000 0.0380 -15.250 -0.9544 0.04436 0.04020 -0.0910 1.0000 0.0381 -15.000 -0.9622 0.03916 0.03483 -0.0964 1.0000 0.0382 -14.750 -0.9659 0.03553 0.03106 -0.0994 1.0000 0.0384 -14.500 -0.9671 0.03299 0.02840 -0.1004 1.0000 0.0386 -14.250 -0.9685 0.03116 0.02647 -0.0996 1.0000 0.0388 -14.000 -0.9686 0.02980 0.02502 -0.0978 0.9959 0.0390 -13.750 -0.9467 0.02825 0.02334 -0.0993 0.9872 0.0393 -13.500 -0.9236 0.02689 0.02185 -0.1004 0.9785 0.0397 -13.250 -0.9041 0.02577 0.02061 -0.1004 0.9676 0.0400 -13.000 -0.8890 0.02488 0.01959 -0.0990 0.9549 0.0403 -12.750 -0.8754 0.02394 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0.6644 0.01100 0.00437 -0.0892 0.5038 0.5370 1.750 0.6874 0.01038 0.00449 -0.0881 0.5011 0.7574 2.000 0.7080 0.01010 0.00461 -0.0859 0.4981 0.9059 2.250 0.7480 0.01011 0.00464 -0.0881 0.4947 0.9727 2.500 0.7949 0.01023 0.00469 -0.0920 0.4911 0.9960 2.750 0.8284 0.01036 0.00477 -0.0933 0.4879 1.0000 3.000 0.8541 0.01040 0.00482 -0.0928 0.4849 1.0000 3.250 0.8802 0.01045 0.00486 -0.0925 0.4814 1.0000 3.500 0.9066 0.01051 0.00489 -0.0922 0.4779 1.0000 3.750 0.9332 0.01059 0.00493 -0.0919 0.4742 1.0000 4.000 0.9600 0.01075 0.00502 -0.0917 0.4703 1.0000 4.250 0.9869 0.01078 0.00510 -0.0916 0.4664 1.0000 4.500 1.0139 0.01083 0.00516 -0.0914 0.4618 1.0000 4.750 1.0407 0.01091 0.00520 -0.0912 0.4569 1.0000 5.000 1.0672 0.01103 0.00528 -0.0910 0.4516 1.0000 5.250 1.0942 0.01108 0.00536 -0.0909 0.4449 1.0000 5.500 1.1201 0.01119 0.00542 -0.0906 0.4375 1.0000 5.750 1.1466 0.01129 0.00554 -0.0905 0.4295 1.0000 6.000 1.1719 0.01143 0.00563 -0.0901 0.4202 1.0000 6.250 1.1976 0.01158 0.00578 -0.0898 0.4091 1.0000 6.500 1.2217 0.01180 0.00594 -0.0893 0.3959 1.0000 6.750 1.2444 0.01210 0.00616 -0.0886 0.3809 1.0000 7.000 1.2659 0.01247 0.00645 -0.0877 0.3664 1.0000 7.500 1.3070 0.01331 0.00716 -0.0856 0.3426 1.0000 7.750 1.3265 0.01377 0.00756 -0.0845 0.3335 1.0000 8.000 1.3455 0.01422 0.00798 -0.0832 0.3253 1.0000 8.250 1.3631 0.01469 0.00842 -0.0818 0.3184 1.0000 8.500 1.3801 0.01511 0.00884 -0.0801 0.3125 1.0000 8.750 1.3941 0.01566 0.00936 -0.0781 0.3070 1.0000 9.000 1.4102 0.01618 0.00989 -0.0766 0.3023 1.0000 9.250 1.4283 0.01665 0.01038 -0.0754 0.2981 1.0000 9.500 1.4444 0.01723 0.01097 -0.0740 0.2941 1.0000 9.750 1.4582 0.01795 0.01167 -0.0724 0.2901 1.0000 10.000 1.4739 0.01860 0.01235 -0.0711 0.2865 1.0000 10.250 1.4919 0.01915 0.01295 -0.0702 0.2829 1.0000 10.500 1.5073 0.01986 0.01368 -0.0690 0.2789 1.0000 10.750 1.5205 0.02073 0.01455 -0.0677 0.2753 1.0000 11.000 1.5319 0.02174 0.01555 -0.0663 0.2716 1.0000 11.250 1.5492 0.02242 0.01631 -0.0656 0.2690 1.0000 11.500 1.5645 0.02324 0.01719 -0.0647 0.2653 1.0000 11.750 1.5773 0.02427 0.01824 -0.0637 0.2617 1.0000 12.000 1.5876 0.02548 0.01946 -0.0626 0.2584 1.0000 12.250 1.5981 0.02672 0.02073 -0.0615 0.2554 1.0000 12.500 1.6129 0.02771 0.02180 -0.0609 0.2529 1.0000 12.750 1.6259 0.02884 0.02300 -0.0603 0.2499 1.0000 13.000 1.6361 0.03021 0.02442 -0.0595 0.2465 1.0000 13.250 1.6429 0.03189 0.02611 -0.0586 0.2429 1.0000 13.500 1.6504 0.03354 0.02780 -0.0578 0.2396 1.0000 13.750 1.6620 0.03491 0.02926 -0.0573 0.2365 1.0000 14.000 1.6701 0.03658 0.03100 -0.0567 0.2326 1.0000 14.250 1.6739 0.03869 0.03313 -0.0561 0.2284 1.0000 14.500 1.6777 0.04083 0.03531 -0.0554 0.2247 1.0000 14.750 1.6861 0.04263 0.03720 -0.0551 0.2205 1.0000 15.000 1.6893 0.04492 0.03954 -0.0547 0.2156 1.0000 15.250 1.6878 0.04768 0.04231 -0.0541 0.2108 1.0000 15.500 1.6939 0.04978 0.04451 -0.0538 0.2055 1.0000 15.750 1.6902 0.05290 0.04765 -0.0535 0.1987 1.0000 16.000 1.6887 0.05583 0.05062 -0.0532 0.1895 1.0000 16.250 1.6809 0.05947 0.05426 -0.0529 0.1781 1.0000 16.500 1.6644 0.06417 0.05892 -0.0526 0.1599 1.0000 16.750 1.6333 0.07060 0.06523 -0.0524 0.1381 1.0000 17.000 1.6090 0.07636 0.07094 -0.0524 0.1272 1.0000 17.250 1.5935 0.08117 0.07576 -0.0524 0.1210 1.0000 17.500 1.5795 0.08586 0.08048 -0.0526 0.1168 1.0000 17.750 1.5676 0.09040 0.08506 -0.0529 0.1132 1.0000