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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -1.0674 0.09341 0.08847 -0.0716 0.9999 0.0437 -19.500 -1.0744 0.08980 0.08478 -0.0724 0.9999 0.0442 -19.250 -1.0815 0.08624 0.08114 -0.0732 0.9999 0.0446 -19.000 -1.0884 0.08279 0.07761 -0.0738 0.9999 0.0450 -18.750 -1.0969 0.07923 0.07399 -0.0744 0.9999 0.0454 -18.500 -1.1055 0.07572 0.07043 -0.0749 0.9999 0.0458 -18.250 -1.1135 0.07236 0.06702 -0.0752 0.9999 0.0462 -18.000 -1.1203 0.06925 0.06386 -0.0754 0.9999 0.0467 -17.750 -1.1256 0.06641 0.06095 -0.0753 0.9999 0.0471 -17.500 -1.1234 0.06330 0.05777 -0.0769 0.9993 0.0478 -17.250 -1.1184 0.06045 0.05486 -0.0785 0.9986 0.0484 -17.000 -1.1117 0.05775 0.05207 -0.0803 0.9977 0.0491 -16.750 -1.1030 0.05523 0.04948 -0.0820 0.9967 0.0498 -16.500 -1.0967 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0.5648 2.750 0.7877 0.01450 0.00643 -0.1283 0.1486 0.5676 3.000 0.8100 0.01479 0.00667 -0.1271 0.1388 0.5706 3.250 0.8316 0.01510 0.00693 -0.1257 0.1300 0.5734 3.500 0.8538 0.01539 0.00718 -0.1245 0.1215 0.5758 3.750 0.8765 0.01569 0.00744 -0.1234 0.1144 0.5780 4.000 0.8998 0.01601 0.00774 -0.1224 0.1078 0.5807 4.250 0.9238 0.01629 0.00804 -0.1215 0.1022 0.5834 4.500 0.9474 0.01662 0.00835 -0.1206 0.0968 0.5863 4.750 0.9710 0.01694 0.00867 -0.1197 0.0915 0.5895 5.000 0.9945 0.01728 0.00900 -0.1187 0.0865 0.5926 5.250 1.0176 0.01764 0.00933 -0.1177 0.0813 0.5954 5.500 1.0408 0.01799 0.00967 -0.1168 0.0760 0.5980 5.750 1.0635 0.01838 0.01003 -0.1157 0.0704 0.6003 6.000 1.0859 0.01877 0.01042 -0.1147 0.0644 0.6031 6.250 1.1080 0.01919 0.01083 -0.1135 0.0584 0.6062 6.500 1.1296 0.01965 0.01128 -0.1124 0.0528 0.6095 6.750 1.1508 0.02013 0.01175 -0.1111 0.0476 0.6129 7.000 1.1716 0.02064 0.01225 -0.1098 0.0430 0.6161 7.250 1.1922 0.02117 0.01277 -0.1085 0.0388 0.6191 7.500 1.2124 0.02172 0.01330 -0.1071 0.0352 0.6219 8.000 1.2523 0.02286 0.01445 -0.1044 0.0298 0.6276 8.250 1.2717 0.02347 0.01508 -0.1029 0.0279 0.6309 8.500 1.2912 0.02405 0.01570 -0.1015 0.0263 0.6347 8.750 1.3100 0.02470 0.01638 -0.1000 0.0249 0.6385 9.000 1.3288 0.02533 0.01704 -0.0985 0.0239 0.6423 9.250 1.3471 0.02599 0.01773 -0.0970 0.0229 0.6457 9.500 1.3649 0.02670 0.01847 -0.0954 0.0219 0.6487 9.750 1.3822 0.02745 0.01927 -0.0939 0.0212 0.6523 10.000 1.3995 0.02817 0.02006 -0.0923 0.0206 0.6561 10.250 1.4162 0.02894 0.02088 -0.0906 0.0200 0.6601 10.500 1.4325 0.02975 0.02174 -0.0890 0.0194 0.6642 10.750 1.4477 0.03064 0.02267 -0.0873 0.0189 0.6683 11.000 1.4621 0.03159 0.02367 -0.0855 0.0185 0.6724 11.250 1.4761 0.03258 0.02473 -0.0837 0.0181 0.6770 11.500 1.4900 0.03355 0.02579 -0.0819 0.0178 0.6818 11.750 1.5034 0.03459 0.02690 -0.0802 0.0174 0.6866 12.000 1.5161 0.03569 0.02807 -0.0784 0.0171 0.6911 12.250 1.5279 0.03686 0.02932 -0.0766 0.0168 0.6955 12.500 1.5391 0.03808 0.03064 -0.0748 0.0165 0.7005 12.750 1.5492 0.03941 0.03205 -0.0730 0.0163 0.7059 13.000 1.5588 0.04082 0.03353 -0.0712 0.0160 0.7116 13.250 1.5666 0.04238 0.03518 -0.0694 0.0158 0.7173 13.500 1.5737 0.04405 0.03695 -0.0676 0.0156 0.7240 13.750 1.5785 0.04595 0.03894 -0.0658 0.0154 0.7310 14.000 1.5826 0.04799 0.04107 -0.0641 0.0153 0.7378 14.250 1.5882 0.04994 0.04315 -0.0626 0.0151 0.7453 14.500 1.5923 0.05211 0.04544 -0.0612 0.0150 0.7533 14.750 1.5960 0.05437 0.04782 -0.0600 0.0149 0.7615 15.000 1.5980 0.05688 0.05047 -0.0588 0.0148 0.7711 15.250 1.5986 0.05961 0.05334 -0.0578 0.0147 0.7812 15.500 1.5983 0.06257 0.05644 -0.0571 0.0146 0.7934 15.750 1.5966 0.06578 0.05981 -0.0565 0.0145 0.8075 16.000 1.5933 0.06930 0.06350 -0.0562 0.0143 0.8254 16.250 1.5877 0.07312 0.06751 -0.0561 0.0143 0.8496 16.500 1.5790 0.07711 0.07171 -0.0558 0.0142 0.8895 16.750 1.5629 0.08113 0.07591 -0.0548 0.0141 1.0001 17.000 1.5529 0.08640 0.08132 -0.0563 0.0141 1.0001 17.250 1.5403 0.09233 0.08740 -0.0585 0.0140 1.0001 17.500 1.5259 0.09874 0.09397 -0.0612 0.0140 1.0001 17.750 1.5077 0.10602 0.10142 -0.0647 0.0139 1.0001 18.000 1.4879 0.11382 0.10938 -0.0688 0.0139 1.0001 18.250 1.4663 0.12214 0.11787 -0.0734 0.0139 1.0001 18.500 1.4438 0.13075 0.12665 -0.0786 0.0139 1.0001