XFOIL Version 6.96 Calculated polar for: HQ 3.5/13 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.500 -0.2467 0.09011 0.08709 -0.0521 0.9873 0.0564 -9.250 -0.2414 0.08469 0.08168 -0.0563 0.9847 0.0585 -9.000 -0.2507 0.07728 0.07430 -0.0644 0.9809 0.0613 -8.750 -0.2721 0.06783 0.06484 -0.0758 0.9744 0.0620 -8.500 -0.2928 0.06069 0.05759 -0.0850 0.9665 0.0621 -8.250 -0.3021 0.05468 0.05136 -0.0917 0.9577 0.0623 -8.000 -0.3054 0.04617 0.04280 -0.0949 0.9524 0.0633 -7.750 -0.3988 0.04066 0.03593 -0.0952 0.9485 0.0325 -7.500 -0.3739 0.03671 0.03151 -0.0975 0.9440 0.0319 -7.250 -0.3465 0.03178 0.02596 -0.1005 0.9413 0.0323 -7.000 -0.3295 0.03024 0.02444 -0.1000 0.9335 0.0342 -6.750 -0.2967 0.02828 0.02221 -0.1019 0.9301 0.0360 -6.500 -0.2615 0.02562 0.01908 -0.1040 0.9278 0.0381 -6.250 -0.2336 0.02410 0.01712 -0.1040 0.9228 0.0402 -6.000 -0.2079 0.02219 0.01518 -0.1042 0.9174 0.0440 -5.750 -0.1729 0.02125 0.01400 -0.1056 0.9143 0.0513 -5.500 -0.1374 0.02015 0.01289 -0.1073 0.9120 0.0596 -5.250 -0.1168 0.01939 0.01207 -0.1062 0.9045 0.0661 -5.000 -0.0847 0.01910 0.01167 -0.1071 0.9004 0.0747 -4.750 -0.0519 0.01805 0.01066 -0.1082 0.8975 0.0826 -4.500 -0.0282 0.01770 0.01022 -0.1074 0.8910 0.0883 -4.250 -0.0014 0.01686 0.00943 -0.1072 0.8859 0.0943 -4.000 0.0308 0.01632 0.00883 -0.1080 0.8826 0.1036 -3.750 0.0530 0.01580 0.00838 -0.1071 0.8759 0.1152 -3.500 0.0795 0.01518 0.00785 -0.1070 0.8706 0.1365 -3.250 0.1069 0.01386 0.00721 -0.1076 0.8670 0.2758 -3.000 0.1227 0.01313 0.00745 -0.1058 0.8595 0.5274 -2.750 0.1503 0.01311 0.00750 -0.1052 0.8547 0.5924 -2.500 0.1810 0.01312 0.00749 -0.1051 0.8514 0.6298 -2.250 0.2026 0.01335 0.00770 -0.1036 0.8437 0.6555 -2.000 0.2309 0.01338 0.00770 -0.1031 0.8390 0.6768 -1.750 0.2608 0.01338 0.00764 -0.1029 0.8351 0.6949 -1.500 0.2824 0.01356 0.00781 -0.1014 0.8271 0.7124 -1.250 0.3095 0.01359 0.00786 -0.1004 0.8227 0.7345 -1.000 0.3320 0.01372 0.00801 -0.0987 0.8160 0.7536 -0.750 0.3581 0.01365 0.00790 -0.0978 0.8095 0.7675 -0.500 0.3860 0.01351 0.00770 -0.0973 0.8035 0.7792 -0.250 0.4119 0.01340 0.00755 -0.0967 0.7953 0.7890 0.000 0.4414 0.01319 0.00728 -0.0965 0.7897 0.7962 0.250 0.4666 0.01314 0.00720 -0.0960 0.7811 0.8054 0.500 0.4966 0.01292 0.00693 -0.0959 0.7759 0.8127 0.750 0.5205 0.01288 0.00689 -0.0951 0.7666 0.8218 1.000 0.5500 0.01266 0.00662 -0.0950 0.7605 0.8301 1.250 0.5737 0.01259 0.00657 -0.0941 0.7510 0.8393 1.500 0.6024 0.01246 0.00640 -0.0940 0.7446 0.8492 1.750 0.6259 0.01238 0.00636 -0.0930 0.7358 0.8591 2.000 0.6529 0.01225 0.00622 -0.0926 0.7284 0.8697 2.250 0.6777 0.01214 0.00614 -0.0918 0.7195 0.8820 2.500 0.7028 0.01205 0.00608 -0.0911 0.7110 0.8958 2.750 0.7297 0.01190 0.00595 -0.0905 0.7025 0.9112 3.000 0.7578 0.01180 0.00591 -0.0904 0.6918 0.9319 3.250 0.7966 0.01171 0.00584 -0.0927 0.6810 0.9616 3.500 0.8346 0.01167 0.00576 -0.0949 0.6699 1.0000 3.750 0.8625 0.01172 0.00578 -0.0952 0.6574 1.0000 4.000 0.8895 0.01178 0.00582 -0.0953 0.6434 1.0000 4.250 0.9161 0.01185 0.00585 -0.0952 0.6282 1.0000 4.500 0.9422 0.01194 0.00589 -0.0949 0.6118 1.0000 4.750 0.9664 0.01205 0.00599 -0.0942 0.5921 1.0000 5.000 0.9899 0.01219 0.00606 -0.0934 0.5695 1.0000 5.250 1.0120 0.01240 0.00618 -0.0923 0.5431 1.0000 5.500 1.0323 0.01270 0.00635 -0.0909 0.5117 1.0000 5.750 1.0505 0.01314 0.00658 -0.0892 0.4771 1.0000 6.000 1.0673 0.01367 0.00692 -0.0873 0.4415 1.0000 6.250 1.0835 0.01429 0.00734 -0.0854 0.4106 1.0000 6.500 1.1002 0.01492 0.00780 -0.0836 0.3860 1.0000 6.750 1.1182 0.01550 0.00829 -0.0821 0.3654 1.0000 7.000 1.1365 0.01608 0.00878 -0.0807 0.3488 1.0000 7.250 1.1552 0.01664 0.00928 -0.0793 0.3348 1.0000 7.500 1.1739 0.01720 0.00979 -0.0780 0.3227 1.0000 7.750 1.1923 0.01781 0.01033 -0.0767 0.3114 1.0000 8.000 1.2101 0.01833 0.01086 -0.0752 0.3006 1.0000 8.250 1.2278 0.01889 0.01142 -0.0737 0.2906 1.0000 8.500 1.2463 0.01956 0.01202 -0.0725 0.2816 1.0000 8.750 1.2633 0.02009 0.01264 -0.0709 0.2727 1.0000 9.000 1.2812 0.02074 0.01329 -0.0696 0.2641 1.0000 9.250 1.2972 0.02136 0.01393 -0.0680 0.2553 1.0000 9.500 1.3131 0.02198 0.01463 -0.0664 0.2468 1.0000 9.750 1.3295 0.02271 0.01531 -0.0650 0.2384 1.0000 10.000 1.3412 0.02329 0.01607 -0.0628 0.2296 1.0000 10.250 1.3541 0.02403 0.01681 -0.0610 0.2210 1.0000 10.500 1.3638 0.02471 0.01760 -0.0588 0.2117 1.0000 10.750 1.3728 0.02549 0.01847 -0.0566 0.2017 1.0000 11.000 1.3806 0.02637 0.01937 -0.0545 0.1918 1.0000 11.250 1.3876 0.02731 0.02036 -0.0524 0.1812 1.0000 11.500 1.3947 0.02831 0.02147 -0.0505 0.1691 1.0000 11.750 1.4020 0.02946 0.02267 -0.0488 0.1572 1.0000 12.000 1.4084 0.03075 0.02399 -0.0472 0.1453 1.0000 12.250 1.4141 0.03221 0.02546 -0.0456 0.1347 1.0000 12.500 1.4180 0.03386 0.02710 -0.0440 0.1244 1.0000 12.750 1.4224 0.03557 0.02884 -0.0427 0.1139 1.0000 13.000 1.4278 0.03728 0.03061 -0.0415 0.1042 1.0000 13.250 1.4310 0.03923 0.03261 -0.0403 0.0959 1.0000 13.500 1.4311 0.04151 0.03490 -0.0392 0.0878 1.0000 13.750 1.4348 0.04359 0.03709 -0.0383 0.0788 1.0000 14.000 1.4351 0.04606 0.03963 -0.0375 0.0701 1.0000 14.250 1.4317 0.04902 0.04262 -0.0369 0.0599 1.0000 14.500 1.4244 0.05259 0.04620 -0.0364 0.0492 1.0000 14.750 1.4106 0.05710 0.05069 -0.0362 0.0382 1.0000 15.000 1.3962 0.06196 0.05559 -0.0364 0.0323 1.0000 15.250 1.3827 0.06696 0.06065 -0.0371 0.0286 1.0000 15.500 1.3688 0.07227 0.06607 -0.0381 0.0261 1.0000 15.750 1.3585 0.07733 0.07127 -0.0394 0.0240 1.0000 16.000 1.3463 0.08286 0.07692 -0.0411 0.0228 1.0000 16.250 1.3320 0.08889 0.08305 -0.0432 0.0220 1.0000