XFOIL Version 6.94 Calculated polar for: GRUMMAN K-3 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.5692 0.01011 0.00554 -0.1474 0.8482 0.5768 0.500 0.6293 0.01002 0.00545 -0.1475 0.8285 0.5828 1.000 0.6898 0.00994 0.00530 -0.1475 0.8002 0.5875 1.500 0.7441 0.00983 0.00511 -0.1463 0.7459 0.5951 2.000 0.7594 0.01145 0.00563 -0.1372 0.5180 0.6009 2.500 0.7704 0.01356 0.00672 -0.1284 0.3149 0.6065 3.000 0.7983 0.01490 0.00749 -0.1229 0.2104 0.6119 3.500 0.8367 0.01583 0.00817 -0.1193 0.1686 0.6169 4.000 0.8808 0.01668 0.00886 -0.1169 0.1460 0.6207 4.500 0.9283 0.01728 0.00945 -0.1152 0.1309 0.6293 5.000 0.9745 0.01800 0.01016 -0.1132 0.1183 0.6356 5.500 1.0201 0.01876 0.01091 -0.1111 0.1072 0.6418 6.000 1.0649 0.01957 0.01169 -0.1090 0.0964 0.6481 6.500 1.1110 0.02033 0.01244 -0.1070 0.0847 0.6536 7.000 1.1556 0.02115 0.01325 -0.1049 0.0714 0.6614 7.500 1.1967 0.02220 0.01427 -0.1023 0.0568 0.6693 8.000 1.2344 0.02355 0.01558 -0.0992 0.0454 0.6767 8.500 1.2698 0.02506 0.01709 -0.0958 0.0387 0.6839 9.000 1.3038 0.02669 0.01874 -0.0923 0.0345 0.6896 9.500 1.3351 0.02844 0.02060 -0.0886 0.0317 0.7001 10.000 1.3626 0.03045 0.02269 -0.0846 0.0296 0.7099 10.500 1.3893 0.03259 0.02497 -0.0807 0.0279 0.7193 11.000 1.4131 0.03495 0.02744 -0.0767 0.0267 0.7295 11.500 1.4305 0.03784 0.03049 -0.0723 0.0257 0.7409 12.000 1.4504 0.04066 0.03350 -0.0686 0.0248 0.7523 12.500 1.4666 0.04378 0.03682 -0.0648 0.0240 0.7666 13.000 1.4776 0.04751 0.04068 -0.0612 0.0233 0.7824 13.500 1.4846 0.05180 0.04522 -0.0577 0.0228 0.8027 14.000 1.4916 0.05626 0.05002 -0.0548 0.0223 0.8309 14.500 1.4915 0.06114 0.05526 -0.0517 0.0219 0.8817 15.000 1.4796 0.06612 0.06052 -0.0475 0.0216 1.0001 15.500 1.4773 0.07293 0.06753 -0.0473 0.0213 1.0001 16.000 1.4714 0.08061 0.07542 -0.0482 0.0210 1.0001 16.500 1.4622 0.08915 0.08418 -0.0502 0.0209 1.0001 17.000 1.4502 0.09856 0.09380 -0.0534 0.0207 1.0001 17.500 1.4360 0.10872 0.10418 -0.0577 0.0205 1.0001 18.000 1.4188 0.11974 0.11543 -0.0634 0.0204 1.0001 18.500 1.3990 0.13174 0.12770 -0.0705 0.0203 1.0001 19.000 1.3716 0.14610 0.14238 -0.0805 0.0203 1.0001 19.500 1.3174 0.16814 0.16493 -0.0978 0.0204 1.0001