XFOIL Version 6.96 Calculated polar for: HQ 3.5/14 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.750 -0.3768 0.09642 0.09152 -0.0547 1.0000 0.0388 -10.500 -0.3909 0.09291 0.08811 -0.0543 1.0000 0.0393 -10.000 -0.5209 0.05886 0.05375 -0.0825 0.9802 0.0364 -9.750 -0.5128 0.05552 0.05030 -0.0869 0.9718 0.0372 -9.500 -0.5023 0.05271 0.04735 -0.0897 0.9628 0.0381 -9.250 -0.4954 0.04914 0.04352 -0.0924 0.9539 0.0391 -9.000 -0.4833 0.04534 0.03932 -0.0954 0.9471 0.0408 -8.750 -0.4778 0.04159 0.03504 -0.0961 0.9376 0.0427 -8.500 -0.4622 0.03751 0.03020 -0.0978 0.9318 0.0447 -8.250 -0.4443 0.03608 0.02871 -0.0975 0.9240 0.0460 -8.000 -0.4184 0.03483 0.02731 -0.0986 0.9190 0.0484 -7.750 -0.3938 0.03301 0.02514 -0.0993 0.9142 0.0509 -7.500 -0.3743 0.03122 0.02294 -0.0987 0.9071 0.0528 -7.250 -0.3465 0.02962 0.02108 -0.0995 0.9032 0.0554 -7.000 -0.3211 0.02865 0.02005 -0.0997 0.8981 0.0579 -6.750 -0.2966 0.02758 0.01880 -0.0995 0.8922 0.0603 -6.500 -0.2666 0.02649 0.01745 -0.1001 0.8885 0.0637 -6.250 -0.2388 0.02544 0.01627 -0.1004 0.8845 0.0669 -6.000 -0.2163 0.02469 0.01552 -0.0998 0.8784 0.0697 -5.750 -0.1876 0.02390 0.01465 -0.1001 0.8746 0.0735 -5.500 -0.1561 0.02324 0.01378 -0.1008 0.8717 0.0784 -5.250 -0.1366 0.02255 0.01319 -0.0997 0.8648 0.0822 -5.000 -0.1100 0.02195 0.01255 -0.0996 0.8604 0.0874 -4.750 -0.0806 0.02137 0.01189 -0.1000 0.8573 0.0940 -4.500 -0.0594 0.02090 0.01146 -0.0991 0.8515 0.1004 -4.250 -0.0348 0.02050 0.01099 -0.0987 0.8461 0.1084 -4.000 -0.0060 0.01988 0.01039 -0.0991 0.8422 0.1207 -3.750 0.0163 0.01946 0.01007 -0.0984 0.8360 0.1363 -3.500 0.0406 0.01894 0.00978 -0.0981 0.8303 0.1809 -3.250 0.0686 0.01806 0.00929 -0.0987 0.8264 0.2751 -3.000 0.0854 0.01741 0.00948 -0.0971 0.8194 0.4551 -2.750 0.1111 0.01737 0.00951 -0.0964 0.8140 0.5326 -2.500 0.1401 0.01736 0.00951 -0.0961 0.8105 0.5757 -2.250 0.1609 0.01757 0.00974 -0.0945 0.8037 0.6040 -2.000 0.1870 0.01767 0.00980 -0.0938 0.7984 0.6295 -1.750 0.2173 0.01766 0.00971 -0.0937 0.7946 0.6502 -1.500 0.2373 0.01788 0.00991 -0.0920 0.7869 0.6697 -1.250 0.2640 0.01795 0.00993 -0.0914 0.7821 0.6887 -1.000 0.2936 0.01791 0.00984 -0.0912 0.7788 0.7035 -0.750 0.3132 0.01810 0.01003 -0.0896 0.7716 0.7139 -0.500 0.3410 0.01809 0.00995 -0.0895 0.7669 0.7240 -0.250 0.3719 0.01796 0.00978 -0.0897 0.7633 0.7325 0.000 0.3928 0.01808 0.00989 -0.0885 0.7553 0.7413 0.250 0.4222 0.01794 0.00970 -0.0884 0.7497 0.7496 0.500 0.4480 0.01790 0.00963 -0.0880 0.7428 0.7578 0.750 0.4745 0.01782 0.00954 -0.0875 0.7356 0.7656 1.000 0.5052 0.01766 0.00933 -0.0878 0.7300 0.7732 1.250 0.5278 0.01770 0.00939 -0.0868 0.7212 0.7806 1.500 0.5604 0.01750 0.00913 -0.0873 0.7156 0.7886 1.750 0.5812 0.01761 0.00929 -0.0860 0.7063 0.7972 2.000 0.6116 0.01747 0.00913 -0.0863 0.7005 0.8062 2.250 0.6336 0.01755 0.00927 -0.0852 0.6912 0.8164 2.500 0.6637 0.01736 0.00907 -0.0852 0.6840 0.8259 2.750 0.6849 0.01743 0.00920 -0.0840 0.6732 0.8373 3.000 0.7118 0.01733 0.00913 -0.0836 0.6646 0.8493 3.250 0.7354 0.01731 0.00917 -0.0826 0.6546 0.8628 3.500 0.7587 0.01730 0.00925 -0.0816 0.6443 0.8795 3.750 0.7871 0.01717 0.00917 -0.0815 0.6338 0.9009 4.000 0.8191 0.01707 0.00913 -0.0822 0.6199 0.9370 4.250 0.8493 0.01706 0.00911 -0.0828 0.6036 1.0000 4.500 0.8726 0.01720 0.00924 -0.0822 0.5854 1.0000 4.750 0.8961 0.01735 0.00936 -0.0816 0.5668 1.0000 5.000 0.9197 0.01750 0.00944 -0.0809 0.5466 1.0000 5.250 0.9433 0.01767 0.00953 -0.0802 0.5255 1.0000 5.500 0.9659 0.01792 0.00970 -0.0793 0.5043 1.0000 5.750 0.9885 0.01821 0.00987 -0.0785 0.4844 1.0000 6.000 1.0105 0.01857 0.01010 -0.0775 0.4654 1.0000 6.250 1.0315 0.01901 0.01044 -0.0765 0.4474 1.0000 6.500 1.0516 0.01949 0.01085 -0.0754 0.4300 1.0000 6.750 1.0706 0.02000 0.01132 -0.0741 0.4127 1.0000 7.000 1.0881 0.02053 0.01185 -0.0727 0.3948 1.0000 7.250 1.1035 0.02106 0.01239 -0.0709 0.3761 1.0000 7.500 1.1180 0.02161 0.01294 -0.0690 0.3573 1.0000 7.750 1.1317 0.02223 0.01350 -0.0670 0.3401 1.0000 8.000 1.1448 0.02293 0.01411 -0.0650 0.3248 1.0000 8.250 1.1580 0.02370 0.01481 -0.0631 0.3106 1.0000 8.500 1.1718 0.02449 0.01557 -0.0614 0.2974 1.0000 8.750 1.1857 0.02533 0.01638 -0.0598 0.2849 1.0000 9.000 1.1994 0.02621 0.01722 -0.0582 0.2736 1.0000 9.250 1.2137 0.02705 0.01815 -0.0568 0.2620 1.0000 9.500 1.2275 0.02794 0.01909 -0.0553 0.2512 1.0000 9.750 1.2400 0.02891 0.02004 -0.0538 0.2415 1.0000 10.000 1.2536 0.02982 0.02106 -0.0524 0.2316 1.0000 10.250 1.2668 0.03081 0.02209 -0.0511 0.2235 1.0000 10.500 1.2792 0.03183 0.02319 -0.0497 0.2154 1.0000 10.750 1.2907 0.03290 0.02432 -0.0483 0.2072 1.0000 11.000 1.2999 0.03410 0.02553 -0.0468 0.1994 1.0000 11.250 1.3097 0.03531 0.02683 -0.0455 0.1910 1.0000 11.500 1.3165 0.03672 0.02818 -0.0440 0.1836 1.0000 11.750 1.3250 0.03809 0.02972 -0.0428 0.1754 1.0000 12.000 1.3314 0.03964 0.03123 -0.0415 0.1688 1.0000 12.250 1.3403 0.04111 0.03287 -0.0405 0.1620 1.0000 12.500 1.3471 0.04273 0.03454 -0.0394 0.1563 1.0000 12.750 1.3548 0.04436 0.03630 -0.0384 0.1506 1.0000 13.000 1.3609 0.04614 0.03823 -0.0375 0.1446 1.0000 13.250 1.3651 0.04807 0.04018 -0.0366 0.1394 1.0000 13.500 1.3697 0.05009 0.04248 -0.0358 0.1329 1.0000 13.750 1.3706 0.05242 0.04490 -0.0352 0.1269 1.0000 14.000 1.3719 0.05486 0.04754 -0.0347 0.1200 1.0000 14.250 1.3693 0.05774 0.05053 -0.0344 0.1130 1.0000 14.500 1.3673 0.06077 0.05374 -0.0343 0.1048 1.0000 14.750 1.3612 0.06438 0.05741 -0.0346 0.0970 1.0000 15.000 1.3547 0.06827 0.06142 -0.0351 0.0883 1.0000 15.250 1.3474 0.07245 0.06571 -0.0359 0.0800 1.0000 15.500 1.3373 0.07720 0.07052 -0.0370 0.0734 1.0000 15.750 1.3268 0.08223 0.07564 -0.0384 0.0674 1.0000 16.000 1.3153 0.08762 0.08112 -0.0402 0.0628 1.0000 16.250 1.3031 0.09332 0.08693 -0.0423 0.0586 1.0000 16.500 1.2885 0.09961 0.09329 -0.0448 0.0559 1.0000 16.750 1.2770 0.10553 0.09935 -0.0473 0.0528 1.0000