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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -1.1881 0.07817 0.07390 -0.0754 0.9999 0.0433 -19.500 -1.1959 0.07493 0.07060 -0.0757 0.9999 0.0437 -19.250 -1.2037 0.07172 0.06732 -0.0759 0.9999 0.0441 -19.000 -1.2088 0.06890 0.06444 -0.0759 0.9999 0.0445 -18.750 -1.2136 0.06616 0.06162 -0.0758 0.9999 0.0448 -18.500 -1.2178 0.06353 0.05892 -0.0756 0.9999 0.0451 -18.250 -1.2295 0.06019 0.05553 -0.0754 0.9999 0.0457 -18.000 -1.2386 0.05720 0.05250 -0.0750 0.9999 0.0461 -17.750 -1.2457 0.05451 0.04976 -0.0745 0.9999 0.0466 -17.500 -1.2426 0.05201 0.04722 -0.0754 0.9996 0.0473 -17.250 -1.2354 0.04947 0.04463 -0.0770 0.9989 0.0480 -17.000 -1.2247 0.04735 0.04246 -0.0785 0.9982 0.0487 -16.750 -1.2130 0.04525 0.04029 -0.0801 0.9973 0.0494 -16.500 -1.1999 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0.00253 -0.1534 0.8735 0.5003 -2.000 0.3645 0.00647 0.00246 -0.1534 0.8617 0.5054 -1.750 0.3945 0.00648 0.00243 -0.1536 0.8512 0.5095 -1.500 0.4252 0.00647 0.00241 -0.1539 0.8426 0.5147 -1.250 0.4557 0.00648 0.00243 -0.1543 0.8347 0.5194 -1.000 0.4859 0.00651 0.00246 -0.1545 0.8247 0.5243 -0.750 0.5160 0.00656 0.00248 -0.1547 0.8156 0.5282 -0.500 0.5459 0.00661 0.00250 -0.1548 0.8046 0.5312 -0.250 0.5758 0.00663 0.00252 -0.1550 0.7928 0.5359 0.000 0.6050 0.00671 0.00258 -0.1550 0.7782 0.5418 0.250 0.6332 0.00684 0.00266 -0.1547 0.7584 0.5467 0.500 0.6602 0.00701 0.00273 -0.1542 0.7280 0.5500 0.750 0.6791 0.00754 0.00289 -0.1521 0.6435 0.5524 1.000 0.6877 0.00870 0.00337 -0.1481 0.5048 0.5539 1.250 0.7028 0.00953 0.00374 -0.1456 0.4007 0.5574 1.500 0.7211 0.01021 0.00406 -0.1437 0.3199 0.5609 1.750 0.7414 0.01079 0.00437 -0.1421 0.2584 0.5637 2.000 0.7627 0.01130 0.00465 -0.1408 0.2110 0.5662 2.250 0.7860 0.01168 0.00489 -0.1397 0.1814 0.5688 2.500 0.8097 0.01204 0.00512 -0.1388 0.1601 0.5715 2.750 0.8338 0.01235 0.00534 -0.1379 0.1446 0.5739 3.000 0.8584 0.01262 0.00555 -0.1370 0.1339 0.5758 3.250 0.8832 0.01286 0.00575 -0.1362 0.1259 0.5773 3.500 0.9078 0.01309 0.00595 -0.1354 0.1185 0.5814 3.750 0.9328 0.01329 0.00616 -0.1347 0.1134 0.5848 4.000 0.9558 0.01355 0.00640 -0.1335 0.1076 0.5878 4.250 0.9782 0.01376 0.00661 -0.1322 0.1031 0.5905 4.500 0.9993 0.01404 0.00686 -0.1307 0.0981 0.5931 4.750 1.0226 0.01428 0.00710 -0.1296 0.0940 0.5956 5.000 1.0457 0.01458 0.00737 -0.1285 0.0891 0.5979 5.250 1.0695 0.01486 0.00763 -0.1275 0.0842 0.5998 5.500 1.0931 0.01516 0.00791 -0.1266 0.0792 0.6030 5.750 1.1164 0.01547 0.00821 -0.1256 0.0736 0.6072 6.000 1.1393 0.01582 0.00853 -0.1245 0.0675 0.6104 6.250 1.1619 0.01619 0.00888 -0.1234 0.0613 0.6134 6.500 1.1838 0.01660 0.00926 -0.1221 0.0549 0.6163 6.750 1.2050 0.01704 0.00967 -0.1208 0.0485 0.6191 7.000 1.2258 0.01752 0.01011 -0.1194 0.0426 0.6217 7.250 1.2463 0.01802 0.01057 -0.1179 0.0376 0.6238 7.500 1.2671 0.01851 0.01105 -0.1166 0.0336 0.6280 7.750 1.2876 0.01902 0.01157 -0.1152 0.0307 0.6321 8.000 1.3071 0.01960 0.01214 -0.1136 0.0282 0.6356 8.250 1.3277 0.02007 0.01264 -0.1122 0.0266 0.6390 8.500 1.3469 0.02066 0.01323 -0.1106 0.0250 0.6422 8.750 1.3668 0.02119 0.01378 -0.1092 0.0239 0.6452 9.000 1.3861 0.02174 0.01435 -0.1076 0.0229 0.6476 9.250 1.4048 0.02236 0.01499 -0.1060 0.0219 0.6521 9.500 1.4230 0.02301 0.01569 -0.1044 0.0211 0.6566 9.750 1.4421 0.02358 0.01630 -0.1029 0.0204 0.6609 10.000 1.4602 0.02420 0.01696 -0.1012 0.0199 0.6650 10.250 1.4773 0.02489 0.01768 -0.0995 0.0193 0.6686 10.500 1.4935 0.02567 0.01847 -0.0977 0.0187 0.6716 10.750 1.5075 0.02662 0.01949 -0.0956 0.0182 0.6768 11.000 1.5244 0.02732 0.02025 -0.0939 0.0179 0.6816 11.250 1.5405 0.02808 0.02107 -0.0922 0.0176 0.6862 11.500 1.5559 0.02891 0.02195 -0.0904 0.0174 0.6906 11.750 1.5704 0.02978 0.02287 -0.0885 0.0170 0.6948 12.000 1.5846 0.03069 0.02385 -0.0867 0.0168 0.7010 12.250 1.5982 0.03165 0.02488 -0.0848 0.0165 0.7069 12.500 1.6103 0.03272 0.02600 -0.0829 0.0163 0.7127 12.750 1.6217 0.03388 0.02722 -0.0809 0.0160 0.7183 13.000 1.6310 0.03520 0.02863 -0.0788 0.0158 0.7250 13.250 1.6375 0.03675 0.03026 -0.0765 0.0156 0.7318 13.500 1.6394 0.03870 0.03230 -0.0738 0.0153 0.7378 13.750 1.6477 0.04020 0.03390 -0.0720 0.0152 0.7462 14.000 1.6566 0.04167 0.03546 -0.0702 0.0151 0.7551 14.250 1.6646 0.04325 0.03715 -0.0685 0.0150 0.7648 14.500 1.6709 0.04502 0.03903 -0.0668 0.0149 0.7766 14.750 1.6773 0.04685 0.04098 -0.0653 0.0148 0.7903 15.000 1.6821 0.04889 0.04314 -0.0637 0.0147 0.8066 15.250 1.6854 0.05112 0.04551 -0.0623 0.0146 0.8274 15.750 1.6861 0.05571 0.05048 -0.0588 0.0144 0.9169 16.000 1.6793 0.05805 0.05295 -0.0562 0.0143 1.0001 16.250 1.6776 0.06118 0.05617 -0.0555 0.0143 1.0001 16.500 1.6753 0.06450 0.05958 -0.0550 0.0142 1.0001 16.750 1.6716 0.06814 0.06333 -0.0547 0.0141 1.0001 17.000 1.6657 0.07219 0.06748 -0.0549 0.0140 1.0001 17.250 1.6576 0.07672 0.07213 -0.0554 0.0140 1.0001 17.500 1.6486 0.08158 0.07710 -0.0564 0.0139 1.0001 17.750 1.6360 0.08717 0.08282 -0.0579 0.0139 1.0001 18.000 1.6218 0.09324 0.08902 -0.0600 0.0139 1.0001 18.250 1.6053 0.09985 0.09577 -0.0627 0.0138 1.0001 18.500 1.5864 0.10704 0.10311 -0.0660 0.0138 1.0001 18.750 1.5666 0.11460 0.11082 -0.0698 0.0138 1.0001 19.000 1.5439 0.12281 0.11918 -0.0743 0.0138 1.0001 19.250 1.5215 0.13113 0.12764 -0.0791 0.0137 1.0001