XFOIL Version 6.96 Calculated polar for: GRUMMAN K-3 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 ------ -------- --------- --------- -------- -------- -------- -19.750 -1.1907 0.07471 0.07020 -0.0803 0.9984 0.0367 -19.500 -1.1956 0.07066 0.06608 -0.0824 0.9979 0.0371 -19.250 -1.1969 0.06712 0.06248 -0.0843 0.9973 0.0375 -19.000 -1.1969 0.06373 0.05903 -0.0861 0.9967 0.0379 -18.750 -1.1954 0.06050 0.05573 -0.0880 0.9961 0.0383 -18.500 -1.1903 0.05772 0.05289 -0.0897 0.9956 0.0389 -18.250 -1.1850 0.05495 0.05006 -0.0914 0.9950 0.0394 -18.000 -1.1776 0.05249 0.04754 -0.0930 0.9945 0.0399 -17.750 -1.1695 0.05012 0.04511 -0.0946 0.9941 0.0404 -17.500 -1.1610 0.04781 0.04275 -0.0961 0.9936 0.0409 -17.250 -1.1532 0.04541 0.04031 -0.0977 0.9931 0.0415 -17.000 -1.1436 0.04325 0.03811 -0.0992 0.9926 0.0421 -16.750 -1.1356 0.04129 0.03610 -0.1000 0.9914 0.0427 -16.500 -1.1250 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0.00209 -0.1509 0.8275 0.4476 -2.000 0.3563 0.00654 0.00207 -0.1511 0.8065 0.4569 -1.750 0.3852 0.00662 0.00207 -0.1510 0.7839 0.4655 -1.500 0.4146 0.00669 0.00209 -0.1512 0.7653 0.4720 -1.250 0.4439 0.00677 0.00212 -0.1513 0.7457 0.4787 -1.000 0.4713 0.00694 0.00218 -0.1510 0.7192 0.4856 -0.750 0.4920 0.00744 0.00232 -0.1493 0.6328 0.4900 -0.500 0.5081 0.00829 0.00268 -0.1469 0.5175 0.4950 -0.250 0.5292 0.00888 0.00294 -0.1455 0.4402 0.4998 0.000 0.5513 0.00941 0.00318 -0.1443 0.3708 0.5061 0.250 0.5747 0.00985 0.00339 -0.1434 0.3163 0.5120 0.750 0.6233 0.01062 0.00381 -0.1418 0.2289 0.5220 1.000 0.6485 0.01093 0.00399 -0.1412 0.1998 0.5250 1.250 0.6737 0.01123 0.00417 -0.1406 0.1758 0.5278 1.500 0.6995 0.01149 0.00434 -0.1400 0.1588 0.5301 1.750 0.7256 0.01172 0.00451 -0.1395 0.1466 0.5319 2.000 0.7518 0.01193 0.00468 -0.1390 0.1354 0.5350 2.250 0.7779 0.01214 0.00486 -0.1385 0.1264 0.5381 2.500 0.8035 0.01238 0.00505 -0.1379 0.1181 0.5411 2.750 0.8290 0.01260 0.00524 -0.1372 0.1100 0.5438 3.000 0.8543 0.01282 0.00543 -0.1365 0.1029 0.5463 3.250 0.8792 0.01306 0.00563 -0.1358 0.0971 0.5487 3.500 0.9042 0.01328 0.00582 -0.1350 0.0919 0.5511 3.750 0.9287 0.01351 0.00603 -0.1341 0.0873 0.5532 4.000 0.9517 0.01375 0.00624 -0.1330 0.0822 0.5554 4.250 0.9740 0.01398 0.00647 -0.1317 0.0771 0.5584 4.500 0.9959 0.01424 0.00671 -0.1303 0.0723 0.5612 4.750 1.0187 0.01453 0.00698 -0.1292 0.0665 0.5638 5.000 1.0419 0.01485 0.00727 -0.1281 0.0606 0.5666 5.250 1.0648 0.01520 0.00759 -0.1270 0.0543 0.5695 5.500 1.0874 0.01556 0.00792 -0.1259 0.0484 0.5723 5.750 1.1096 0.01596 0.00828 -0.1247 0.0426 0.5747 6.000 1.1316 0.01636 0.00864 -0.1234 0.0374 0.5765 6.250 1.1539 0.01676 0.00903 -0.1223 0.0333 0.5791 6.500 1.1761 0.01716 0.00943 -0.1211 0.0303 0.5822 6.750 1.1979 0.01758 0.00984 -0.1199 0.0279 0.5852 7.000 1.2199 0.01798 0.01025 -0.1187 0.0260 0.5885 7.250 1.2414 0.01841 0.01068 -0.1174 0.0244 0.5918 7.500 1.2631 0.01882 0.01111 -0.1162 0.0230 0.5949 7.750 1.2840 0.01929 0.01157 -0.1148 0.0216 0.5975 8.000 1.3048 0.01973 0.01203 -0.1134 0.0206 0.5995 8.250 1.3256 0.02019 0.01250 -0.1121 0.0196 0.6020 8.500 1.3462 0.02068 0.01301 -0.1107 0.0187 0.6055 8.750 1.3665 0.02118 0.01353 -0.1094 0.0180 0.6089 9.000 1.3866 0.02168 0.01406 -0.1080 0.0174 0.6122 9.250 1.4062 0.02220 0.01461 -0.1065 0.0169 0.6156 9.500 1.4253 0.02276 0.01519 -0.1050 0.0163 0.6191 9.750 1.4440 0.02335 0.01579 -0.1034 0.0158 0.6222 10.000 1.4620 0.02398 0.01644 -0.1018 0.0153 0.6246 10.250 1.4805 0.02457 0.01708 -0.1002 0.0150 0.6286 10.500 1.4987 0.02519 0.01774 -0.0987 0.0147 0.6324 10.750 1.5165 0.02584 0.01843 -0.0971 0.0144 0.6361 11.000 1.5333 0.02653 0.01917 -0.0954 0.0141 0.6398 11.250 1.5497 0.02726 0.01993 -0.0937 0.0138 0.6433 11.500 1.5659 0.02802 0.02073 -0.0919 0.0136 0.6465 11.750 1.5812 0.02883 0.02158 -0.0902 0.0133 0.6503 12.000 1.5960 0.02970 0.02250 -0.0884 0.0131 0.6551 12.250 1.6102 0.03061 0.02347 -0.0865 0.0128 0.6599 12.500 1.6231 0.03161 0.02452 -0.0846 0.0126 0.6644 12.750 1.6365 0.03258 0.02554 -0.0827 0.0125 0.6683 13.250 1.6622 0.03463 0.02772 -0.0792 0.0123 0.6768 13.500 1.6742 0.03573 0.02889 -0.0773 0.0121 0.6819 13.750 1.6851 0.03692 0.03015 -0.0755 0.0120 0.6869 14.000 1.6955 0.03818 0.03147 -0.0737 0.0119 0.6917 14.250 1.7056 0.03949 0.03286 -0.0719 0.0118 0.6971 14.500 1.7147 0.04093 0.03438 -0.0701 0.0117 0.7038 14.750 1.7235 0.04241 0.03594 -0.0685 0.0116 0.7106 15.250 1.7380 0.04574 0.03944 -0.0652 0.0114 0.7239 15.500 1.7441 0.04759 0.04137 -0.0636 0.0113 0.7315 16.000 1.7542 0.05165 0.04562 -0.0608 0.0111 0.7475 16.250 1.7571 0.05396 0.04803 -0.0596 0.0111 0.7567 16.500 1.7593 0.05642 0.05060 -0.0584 0.0110 0.7670 17.000 1.7605 0.06196 0.05638 -0.0567 0.0108 0.7956 17.250 1.7592 0.06512 0.05967 -0.0561 0.0108 0.8141 17.500 1.7559 0.06860 0.06332 -0.0558 0.0107 0.8391 17.750 1.7503 0.07239 0.06729 -0.0557 0.0107 0.8765 18.000 1.7361 0.07591 0.07104 -0.0541 0.0106 1.0001 18.250 1.7262 0.08074 0.07598 -0.0550 0.0106 1.0001 18.500 1.7144 0.08605 0.08143 -0.0563 0.0105 1.0001 18.750 1.6994 0.09207 0.08758 -0.0583 0.0105 1.0001 19.000 1.6801 0.09898 0.09465 -0.0610 0.0105 1.0001 19.250 1.6555 0.10702 0.10286 -0.0648 0.0104 1.0001