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 = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -1.1042 0.08617 0.08122 -0.0771 0.9999 0.0521 -19.500 -1.1077 0.08319 0.07818 -0.0777 0.9999 0.0527 -19.250 -1.1119 0.08019 0.07511 -0.0782 0.9999 0.0532 -19.000 -1.1160 0.07725 0.07209 -0.0785 0.9999 0.0538 -18.750 -1.1210 0.07423 0.06897 -0.0789 0.9999 0.0544 -18.500 -1.1254 0.07135 0.06598 -0.0791 0.9999 0.0549 -18.250 -1.1245 0.06950 0.06416 -0.0785 0.9999 0.0556 -18.000 -1.1256 0.06728 0.06193 -0.0782 0.9999 0.0562 -17.750 -1.1268 0.06504 0.05966 -0.0779 0.9999 0.0568 -17.500 -1.1286 0.06275 0.05733 -0.0775 0.9999 0.0574 -17.250 -1.1296 0.06062 0.05515 -0.0770 0.9999 0.0581 -17.000 -1.1314 0.05844 0.05291 -0.0765 0.9999 0.0588 -16.750 -1.1321 0.05644 0.05084 -0.0758 0.9999 0.0595 -16.500 -1.1336 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0.00670 -0.1462 0.9029 0.5311 -2.000 0.3213 0.01113 0.00646 -0.1471 0.8996 0.5362 -1.750 0.3605 0.01060 0.00596 -0.1487 0.8963 0.5413 -1.500 0.4014 0.01004 0.00539 -0.1505 0.8921 0.5471 -1.250 0.4285 0.00979 0.00514 -0.1497 0.8811 0.5513 -1.000 0.4636 0.00950 0.00480 -0.1506 0.8738 0.5554 -0.750 0.4909 0.00941 0.00478 -0.1500 0.8646 0.5606 -0.500 0.5239 0.00934 0.00472 -0.1505 0.8581 0.5662 -0.250 0.5514 0.00937 0.00479 -0.1501 0.8491 0.5709 0.000 0.5834 0.00933 0.00473 -0.1506 0.8413 0.5745 0.250 0.6128 0.00935 0.00474 -0.1506 0.8315 0.5771 0.500 0.6438 0.00921 0.00460 -0.1508 0.8202 0.5810 0.750 0.6713 0.00920 0.00463 -0.1504 0.8057 0.5839 1.000 0.6994 0.00922 0.00464 -0.1500 0.7874 0.5869 1.250 0.7270 0.00929 0.00463 -0.1494 0.7617 0.5900 1.500 0.7514 0.00946 0.00464 -0.1482 0.7181 0.5929 1.750 0.7567 0.01039 0.00489 -0.1432 0.5802 0.5955 2.000 0.7589 0.01162 0.00546 -0.1380 0.4552 0.5981 2.500 0.7809 0.01342 0.00635 -0.1315 0.2770 0.6033 2.750 0.7974 0.01406 0.00672 -0.1293 0.2244 0.6060 3.000 0.8156 0.01455 0.00705 -0.1273 0.1926 0.6086 3.250 0.8343 0.01498 0.00738 -0.1254 0.1726 0.6114 3.750 0.8759 0.01571 0.00799 -0.1224 0.1479 0.6177 4.000 0.8985 0.01606 0.00830 -0.1213 0.1394 0.6206 4.250 0.9210 0.01646 0.00863 -0.1202 0.1316 0.6230 4.500 0.9452 0.01675 0.00892 -0.1194 0.1253 0.6257 4.750 0.9677 0.01713 0.00927 -0.1183 0.1190 0.6290 5.000 0.9917 0.01741 0.00959 -0.1175 0.1136 0.6322 5.500 1.0376 0.01813 0.01031 -0.1154 0.1030 0.6388 5.750 1.0598 0.01855 0.01069 -0.1143 0.0977 0.6420 6.000 1.0835 0.01887 0.01102 -0.1135 0.0922 0.6451 6.250 1.1063 0.01927 0.01139 -0.1125 0.0868 0.6476 6.500 1.1287 0.01965 0.01176 -0.1115 0.0811 0.6513 6.750 1.1510 0.02002 0.01215 -0.1104 0.0749 0.6549 7.000 1.1726 0.02047 0.01259 -0.1092 0.0682 0.6586 7.250 1.1933 0.02099 0.01308 -0.1079 0.0610 0.6623 7.500 1.2137 0.02154 0.01360 -0.1066 0.0537 0.6659 7.750 1.2330 0.02219 0.01420 -0.1051 0.0476 0.6692 8.000 1.2518 0.02286 0.01485 -0.1036 0.0428 0.6725 8.250 1.2701 0.02354 0.01555 -0.1020 0.0392 0.6764 8.500 1.2879 0.02427 0.01628 -0.1003 0.0364 0.6802 8.750 1.3061 0.02496 0.01702 -0.0987 0.0342 0.6843 9.000 1.3224 0.02580 0.01786 -0.0969 0.0324 0.6886 9.250 1.3392 0.02660 0.01870 -0.0952 0.0310 0.6927 9.500 1.3562 0.02737 0.01953 -0.0935 0.0296 0.6971 9.750 1.3699 0.02836 0.02055 -0.0915 0.0286 0.7014 10.000 1.3842 0.02933 0.02159 -0.0895 0.0277 0.7058 10.250 1.3996 0.03022 0.02254 -0.0877 0.0268 0.7106 10.500 1.4138 0.03120 0.02357 -0.0859 0.0261 0.7151 10.750 1.4266 0.03226 0.02470 -0.0840 0.0255 0.7200 11.000 1.4358 0.03361 0.02609 -0.0816 0.0249 0.7251 11.250 1.4455 0.03495 0.02751 -0.0795 0.0245 0.7307 11.500 1.4579 0.03611 0.02876 -0.0776 0.0241 0.7366 11.750 1.4690 0.03735 0.03011 -0.0757 0.0236 0.7426 12.000 1.4791 0.03869 0.03155 -0.0738 0.0232 0.7489 12.250 1.4883 0.04012 0.03306 -0.0719 0.0228 0.7556 12.500 1.4968 0.04163 0.03466 -0.0701 0.0225 0.7623 12.750 1.5036 0.04330 0.03642 -0.0682 0.0222 0.7698 13.000 1.5092 0.04512 0.03831 -0.0663 0.0219 0.7781 13.250 1.5120 0.04722 0.04051 -0.0644 0.0216 0.7865 13.500 1.5117 0.04971 0.04310 -0.0623 0.0214 0.7963 13.750 1.5159 0.05183 0.04536 -0.0608 0.0212 0.8078 14.000 1.5202 0.05398 0.04766 -0.0594 0.0211 0.8221 14.250 1.5231 0.05626 0.05011 -0.0580 0.0209 0.8400 14.500 1.5242 0.05865 0.05269 -0.0565 0.0207 0.8650 14.750 1.5191 0.06084 0.05509 -0.0539 0.0206 0.9191 15.000 1.5128 0.06329 0.05767 -0.0517 0.0205 1.0001 15.250 1.5129 0.06643 0.06091 -0.0513 0.0203 1.0001 15.500 1.5116 0.06979 0.06438 -0.0511 0.0202 1.0001 15.750 1.5091 0.07341 0.06811 -0.0512 0.0201 1.0001 16.000 1.5058 0.07728 0.07210 -0.0516 0.0199 1.0001 16.250 1.5014 0.08141 0.07634 -0.0522 0.0198 1.0001 16.500 1.4963 0.08578 0.08082 -0.0532 0.0197 1.0001 16.750 1.4900 0.09043 0.08559 -0.0545 0.0196 1.0001 17.000 1.4828 0.09535 0.09064 -0.0562 0.0195 1.0001 17.250 1.4748 0.10053 0.09595 -0.0582 0.0195 1.0001 17.500 1.4661 0.10596 0.10150 -0.0606 0.0194 1.0001 17.750 1.4567 0.11162 0.10730 -0.0633 0.0193 1.0001 18.000 1.4466 0.11752 0.11333 -0.0664 0.0193 1.0001 18.250 1.4354 0.12372 0.11967 -0.0699 0.0193 1.0001 18.500 1.4237 0.13018 0.12628 -0.0738 0.0192 1.0001 18.750 1.4113 0.13694 0.13318 -0.0782 0.0192 1.0001 19.000 1.3968 0.14431 0.14071 -0.0832 0.0192 1.0001