XFOIL Version 6.96 Calculated polar for: GOE 14K 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 ------ -------- --------- --------- -------- -------- -------- -16.250 -0.6069 0.10688 0.10473 -0.0881 0.9833 0.0051 -16.000 -0.6798 0.08976 0.08748 -0.0965 0.9823 0.0049 -15.750 -0.8279 0.06021 0.05757 -0.1126 0.9809 0.0045 -15.500 -0.8648 0.04685 0.04392 -0.1242 0.9800 0.0043 -15.250 -0.8959 0.03805 0.03485 -0.1319 0.9788 0.0045 -15.000 -0.9006 0.03485 0.03148 -0.1330 0.9781 0.0042 -14.750 -0.9193 0.03260 0.02910 -0.1287 0.9742 0.0045 -14.500 -0.9173 0.03109 0.02745 -0.1270 0.9720 0.0043 -14.250 -0.9182 0.02917 0.02540 -0.1250 0.9704 0.0044 -14.000 -0.9148 0.02746 0.02354 -0.1232 0.9691 0.0045 -13.750 -0.9066 0.02599 0.02193 -0.1218 0.9683 0.0046 -13.500 -0.9085 0.02534 0.02123 -0.1168 0.9638 0.0048 -13.250 -0.9028 0.02435 0.02013 -0.1138 0.9607 0.0048 -13.000 -0.8881 0.02350 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0.5690 0.00673 0.00321 -0.0937 0.7688 0.9544 2.000 0.5939 0.00695 0.00336 -0.0931 0.7444 0.9570 2.250 0.5770 0.00743 0.00361 -0.0826 0.6858 0.9656 2.500 0.5827 0.00827 0.00404 -0.0779 0.5967 0.9684 2.750 0.5736 0.00942 0.00462 -0.0701 0.4636 0.9730 3.000 0.5806 0.01005 0.00501 -0.0657 0.4069 0.9770 3.250 0.6091 0.01042 0.00523 -0.0664 0.3688 0.9782 3.500 0.6335 0.01081 0.00545 -0.0661 0.3272 0.9796 3.750 0.6543 0.01128 0.00571 -0.0650 0.2765 0.9816 4.000 0.6694 0.01189 0.00616 -0.0626 0.2371 0.9860 4.250 0.6960 0.01231 0.00636 -0.0629 0.1875 0.9868 4.500 0.7230 0.01260 0.00654 -0.0633 0.1606 0.9877 4.750 0.7429 0.01304 0.00678 -0.0621 0.1181 0.9886 5.000 0.7630 0.01342 0.00702 -0.0610 0.0895 0.9895 5.250 0.7848 0.01372 0.00726 -0.0601 0.0743 0.9905 5.750 0.8283 0.01422 0.00772 -0.0582 0.0621 0.9923 6.000 0.8486 0.01450 0.00797 -0.0571 0.0569 0.9931 6.250 0.8691 0.01479 0.00825 -0.0559 0.0496 0.9941 6.500 0.8912 0.01506 0.00852 -0.0551 0.0462 0.9949 6.750 0.9132 0.01532 0.00875 -0.0543 0.0365 0.9953 7.000 0.9326 0.01572 0.00906 -0.0531 0.0247 0.9957 7.250 0.9531 0.01603 0.00937 -0.0521 0.0204 0.9962 7.500 0.9742 0.01638 0.00970 -0.0512 0.0174 0.9968 7.750 0.9960 0.01669 0.01004 -0.0505 0.0157 0.9975 8.000 1.0154 0.01710 0.01043 -0.0493 0.0132 0.9980 8.250 1.0354 0.01743 0.01079 -0.0482 0.0123 0.9984 8.500 1.0557 0.01783 0.01120 -0.0472 0.0112 0.9989 8.750 1.0769 0.01823 0.01163 -0.0464 0.0100 0.9995 9.000 1.0972 0.01865 0.01208 -0.0455 0.0091 0.9999 9.250 1.1144 0.01906 0.01252 -0.0440 0.0091 1.0000 9.500 1.1294 0.01952 0.01299 -0.0419 0.0085 1.0000 9.750 1.1438 0.02002 0.01354 -0.0398 0.0079 1.0000 10.000 1.1590 0.02046 0.01402 -0.0378 0.0073 1.0000 10.250 1.1736 0.02096 0.01456 -0.0358 0.0073 1.0000 10.500 1.1878 0.02150 0.01514 -0.0337 0.0069 1.0000 10.750 1.2003 0.02217 0.01584 -0.0314 0.0063 1.0000 11.000 1.2145 0.02270 0.01642 -0.0294 0.0063 1.0000 11.250 1.2279 0.02331 0.01709 -0.0273 0.0062 1.0000 11.500 1.2405 0.02398 0.01782 -0.0251 0.0060 1.0000 11.750 1.2540 0.02455 0.01844 -0.0232 0.0056 1.0000 12.000 1.2669 0.02519 0.01915 -0.0212 0.0054 1.0000 12.250 1.2783 0.02594 0.01996 -0.0189 0.0052 1.0000 12.500 1.2889 0.02674 0.02081 -0.0167 0.0050 1.0000 12.750 1.2985 0.02766 0.02179 -0.0143 0.0048 1.0000 13.000 1.3064 0.02867 0.02289 -0.0118 0.0048 1.0000 13.250 1.3173 0.02947 0.02375 -0.0098 0.0046 1.0000 13.500 1.3278 0.03028 0.02462 -0.0077 0.0046 1.0000 13.750 1.3323 0.03158 0.02603 -0.0050 0.0046 1.0000 14.000 1.3413 0.03254 0.02707 -0.0029 0.0045 1.0000 14.250 1.3509 0.03347 0.02807 -0.0010 0.0042 1.0000 14.500 1.3595 0.03450 0.02917 0.0010 0.0041 1.0000 14.750 1.3627 0.03598 0.03075 0.0035 0.0040 1.0000 15.000 1.3700 0.03713 0.03198 0.0055 0.0039 1.0000 15.250 1.3715 0.03878 0.03374 0.0079 0.0040 1.0000 15.500 1.3771 0.04013 0.03518 0.0098 0.0039 1.0000 15.750 1.3811 0.04165 0.03679 0.0117 0.0037 1.0000 16.000 1.3816 0.04352 0.03876 0.0138 0.0036 1.0000 16.250 1.3843 0.04523 0.04055 0.0155 0.0036 1.0000 16.500 1.3791 0.04774 0.04318 0.0176 0.0036 1.0000 16.750 1.3714 0.05062 0.04617 0.0195 0.0034 1.0000 17.000 1.3694 0.05306 0.04874 0.0210 0.0035 1.0000 17.250 1.3649 0.05584 0.05162 0.0221 0.0034 1.0000 17.500 1.3567 0.05921 0.05511 0.0231 0.0034 1.0000 17.750 1.3579 0.06160 0.05762 0.0236 0.0032 1.0000 18.000 1.3344 0.06727 0.06345 0.0238 0.0034 1.0000 18.250 1.3288 0.07092 0.06723 0.0236 0.0033 1.0000 18.500 1.3182 0.07541 0.07185 0.0228 0.0032 1.0000 18.750 1.2971 0.08186 0.07848 0.0211 0.0032 1.0000 19.000 1.2818 0.08774 0.08448 0.0190 0.0032 1.0000 19.250 1.2563 0.09586 0.09278 0.0155 0.0032 1.0000