XFOIL Version 6.96 Calculated polar for: GOE 796 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -14.500 -0.7184 0.09505 0.09285 -0.0435 1.0000 0.0126 -14.250 -0.7933 0.07833 0.07598 -0.0538 1.0000 0.0125 -14.000 -0.9955 0.03555 0.03243 -0.0901 1.0000 0.0118 -13.750 -1.0103 0.03312 0.02988 -0.0876 0.9999 0.0118 -13.500 -0.9952 0.03086 0.02748 -0.0893 0.9950 0.0120 -13.250 -0.9776 0.02911 0.02561 -0.0903 0.9899 0.0121 -13.000 -0.9582 0.02761 0.02400 -0.0910 0.9853 0.0122 -12.750 -0.9381 0.02629 0.02257 -0.0915 0.9810 0.0123 -12.500 -0.9188 0.02509 0.02127 -0.0914 0.9755 0.0124 -12.000 -0.8789 0.02298 0.01894 -0.0909 0.9651 0.0127 -11.750 -0.8587 0.02205 0.01790 -0.0904 0.9598 0.0128 -11.500 -0.8380 0.02120 0.01694 -0.0899 0.9547 0.0129 -11.250 -0.8166 0.02044 0.01609 -0.0893 0.9491 0.0131 -11.000 -0.7947 0.01974 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0.2165 0.00811 0.00153 -0.0829 0.6383 0.0873 -1.250 0.2449 0.00809 0.00150 -0.0830 0.6311 0.0948 -1.000 0.2736 0.00806 0.00146 -0.0832 0.6248 0.0989 -0.500 0.3306 0.00799 0.00141 -0.0834 0.6132 0.1106 -0.250 0.3590 0.00795 0.00139 -0.0835 0.6063 0.1202 0.000 0.3872 0.00794 0.00138 -0.0835 0.5963 0.1273 0.250 0.4151 0.00794 0.00137 -0.0836 0.5828 0.1391 0.500 0.4428 0.00791 0.00138 -0.0836 0.5701 0.1624 0.750 0.4706 0.00786 0.00139 -0.0836 0.5590 0.1962 1.000 0.4985 0.00782 0.00141 -0.0837 0.5481 0.2299 1.250 0.5260 0.00778 0.00145 -0.0837 0.5355 0.2714 1.750 0.5788 0.00755 0.00157 -0.0834 0.4970 0.4509 2.000 0.6045 0.00750 0.00167 -0.0832 0.4719 0.5421 2.250 0.6288 0.00739 0.00179 -0.0827 0.4441 0.6663 2.500 0.6521 0.00734 0.00194 -0.0818 0.4149 0.7780 2.750 0.6711 0.00719 0.00213 -0.0797 0.3927 0.9270 3.000 0.7055 0.00741 0.00229 -0.0811 0.3718 0.9783 3.250 0.7464 0.00765 0.00244 -0.0841 0.3551 0.9956 3.750 0.8076 0.00797 0.00267 -0.0856 0.3354 1.0000 4.250 0.8568 0.00829 0.00291 -0.0843 0.3178 1.0000 4.500 0.8816 0.00847 0.00304 -0.0838 0.3105 1.0000 4.750 0.9067 0.00862 0.00317 -0.0833 0.3014 1.0000 5.000 0.9310 0.00886 0.00333 -0.0826 0.2858 1.0000 5.250 0.9548 0.00913 0.00351 -0.0820 0.2673 1.0000 5.500 0.9781 0.00945 0.00371 -0.0812 0.2422 1.0000 5.750 0.9971 0.01009 0.00406 -0.0798 0.1915 1.0000 6.250 1.0416 0.01088 0.00465 -0.0780 0.1550 1.0000 6.500 1.0656 0.01115 0.00490 -0.0774 0.1477 1.0000 6.750 1.0900 0.01138 0.00512 -0.0769 0.1422 1.0000 7.000 1.1135 0.01167 0.00537 -0.0762 0.1350 1.0000 7.250 1.1374 0.01192 0.00561 -0.0756 0.1278 1.0000 7.500 1.1600 0.01226 0.00590 -0.0748 0.1180 1.0000 7.750 1.1817 0.01264 0.00621 -0.0739 0.1048 1.0000 8.000 1.2018 0.01313 0.00659 -0.0727 0.0880 1.0000 8.250 1.2218 0.01359 0.00699 -0.0716 0.0761 1.0000 8.500 1.2422 0.01401 0.00738 -0.0704 0.0685 1.0000 8.750 1.2625 0.01440 0.00775 -0.0693 0.0626 1.0000 9.000 1.2818 0.01482 0.00815 -0.0680 0.0568 1.0000 9.250 1.2992 0.01525 0.00856 -0.0663 0.0515 1.0000 9.500 1.3167 0.01567 0.00899 -0.0647 0.0476 1.0000 9.750 1.3326 0.01620 0.00949 -0.0629 0.0414 1.0000 10.000 1.3472 0.01682 0.01007 -0.0609 0.0335 1.0000 10.250 1.3592 0.01761 0.01080 -0.0587 0.0236 1.0000 10.500 1.3730 0.01833 0.01150 -0.0568 0.0193 1.0000 10.750 1.3881 0.01898 0.01217 -0.0552 0.0171 1.0000 11.000 1.4035 0.01962 0.01284 -0.0536 0.0158 1.0000 11.250 1.4179 0.02034 0.01359 -0.0520 0.0146 1.0000 11.500 1.4330 0.02104 0.01432 -0.0506 0.0138 1.0000 11.750 1.4479 0.02175 0.01507 -0.0492 0.0129 1.0000 12.000 1.4615 0.02257 0.01593 -0.0477 0.0119 1.0000 12.250 1.4742 0.02348 0.01687 -0.0462 0.0109 1.0000 12.500 1.4872 0.02438 0.01781 -0.0448 0.0099 1.0000 12.750 1.4988 0.02541 0.01887 -0.0434 0.0088 1.0000 13.000 1.5096 0.02654 0.02002 -0.0420 0.0083 1.0000 13.250 1.5198 0.02773 0.02125 -0.0406 0.0079 1.0000 13.500 1.5295 0.02899 0.02256 -0.0393 0.0077 1.0000 13.750 1.5386 0.03036 0.02398 -0.0380 0.0074 1.0000 14.000 1.5468 0.03182 0.02550 -0.0368 0.0071 1.0000 14.250 1.5543 0.03338 0.02713 -0.0357 0.0069 1.0000 14.500 1.5611 0.03505 0.02886 -0.0346 0.0067 1.0000 14.750 1.5686 0.03671 0.03059 -0.0337 0.0066 1.0000 15.000 1.5750 0.03848 0.03244 -0.0328 0.0065 1.0000 15.250 1.5805 0.04039 0.03442 -0.0320 0.0063 1.0000 15.500 1.5852 0.04244 0.03656 -0.0312 0.0062 1.0000 15.750 1.5889 0.04465 0.03885 -0.0306 0.0060 1.0000 16.000 1.5915 0.04701 0.04129 -0.0300 0.0058 1.0000 16.250 1.5931 0.04954 0.04391 -0.0296 0.0057 1.0000 16.500 1.5934 0.05229 0.04674 -0.0292 0.0055 1.0000 16.750 1.5924 0.05527 0.04981 -0.0290 0.0054 1.0000 17.000 1.5899 0.05847 0.05310 -0.0289 0.0052 1.0000 17.250 1.5853 0.06202 0.05674 -0.0290 0.0051 1.0000 17.500 1.5790 0.06593 0.06075 -0.0293 0.0050 1.0000 17.750 1.5765 0.06941 0.06433 -0.0297 0.0049 1.0000 18.000 1.5732 0.07306 0.06808 -0.0302 0.0048 1.0000 18.250 1.5679 0.07706 0.07219 -0.0309 0.0048 1.0000 18.500 1.5617 0.08128 0.07650 -0.0318 0.0047 1.0000 18.750 1.5542 0.08577 0.08111 -0.0329 0.0046 1.0000 19.000 1.5451 0.09058 0.08603 -0.0342 0.0045 1.0000 19.250 1.5352 0.09557 0.09112 -0.0356 0.0044 1.0000