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 = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.750 -0.8987 0.06884 0.06609 -0.0775 1.0000 0.0061 -16.500 -0.9606 0.05376 0.05068 -0.0881 1.0000 0.0059 -16.250 -0.9827 0.04737 0.04413 -0.0923 1.0000 0.0058 -16.000 -1.0017 0.04203 0.03864 -0.0955 1.0000 0.0059 -15.750 -1.0134 0.03800 0.03449 -0.0974 1.0000 0.0060 -15.500 -1.0203 0.03487 0.03125 -0.0985 1.0000 0.0061 -15.250 -1.0266 0.03210 0.02838 -0.0988 1.0000 0.0062 -15.000 -1.0299 0.02997 0.02616 -0.0984 1.0000 0.0063 -14.750 -1.0194 0.02777 0.02385 -0.1003 0.9890 0.0064 -14.500 -0.9984 0.02585 0.02182 -0.1036 0.9828 0.0066 -14.250 -0.9736 0.02414 0.02000 -0.1070 0.9766 0.0068 -14.000 -0.9474 0.02264 0.01839 -0.1102 0.9694 0.0071 -13.750 -0.9236 0.02147 0.01711 -0.1119 0.9600 0.0073 -13.500 -0.9059 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0.6883 0.0556 -3.750 0.0609 0.00847 0.00214 -0.1010 0.6823 0.0602 -3.500 0.0894 0.00837 0.00204 -0.1012 0.6776 0.0643 -3.250 0.1177 0.00827 0.00195 -0.1013 0.6732 0.0699 -3.000 0.1457 0.00820 0.00187 -0.1013 0.6683 0.0759 -2.750 0.1741 0.00812 0.00178 -0.1014 0.6634 0.0820 -2.500 0.2024 0.00802 0.00171 -0.1015 0.6576 0.0909 -2.000 0.2582 0.00775 0.00153 -0.1017 0.6452 0.1350 -1.750 0.2858 0.00756 0.00148 -0.1018 0.6382 0.1935 -1.250 0.3421 0.00736 0.00138 -0.1020 0.6267 0.2366 -1.000 0.3695 0.00716 0.00134 -0.1021 0.6203 0.3013 -0.750 0.3965 0.00675 0.00126 -0.1023 0.6133 0.4106 -0.500 0.4241 0.00665 0.00128 -0.1023 0.6053 0.4752 -0.250 0.4524 0.00666 0.00130 -0.1024 0.5978 0.4890 0.000 0.4799 0.00670 0.00132 -0.1023 0.5857 0.5044 0.250 0.5071 0.00675 0.00135 -0.1022 0.5698 0.5178 0.500 0.5339 0.00686 0.00139 -0.1020 0.5478 0.5273 0.750 0.5585 0.00708 0.00147 -0.1014 0.5104 0.5371 1.000 0.5824 0.00738 0.00160 -0.1007 0.4705 0.5469 1.250 0.6082 0.00754 0.00171 -0.1004 0.4524 0.5567 1.750 0.6613 0.00781 0.00190 -0.1000 0.4290 0.5699 2.250 0.7149 0.00802 0.00209 -0.0997 0.4114 0.5886 2.500 0.7416 0.00813 0.00219 -0.0995 0.4023 0.5994 2.750 0.7683 0.00824 0.00230 -0.0994 0.3917 0.6106 3.000 0.7941 0.00839 0.00243 -0.0990 0.3741 0.6233 3.250 0.8168 0.00873 0.00261 -0.0982 0.3326 0.6352 3.500 0.8400 0.00905 0.00282 -0.0975 0.3093 0.6449 3.750 0.8647 0.00927 0.00300 -0.0970 0.2966 0.6540 4.000 0.8897 0.00946 0.00317 -0.0965 0.2876 0.6618 4.250 0.9151 0.00961 0.00333 -0.0962 0.2805 0.6697 4.500 0.9399 0.00981 0.00350 -0.0957 0.2726 0.6764 4.750 0.9651 0.00996 0.00366 -0.0953 0.2655 0.6830 5.250 1.0146 0.01029 0.00401 -0.0943 0.2528 0.6975 5.500 1.0387 0.01049 0.00420 -0.0937 0.2448 0.7043 5.750 1.0627 0.01068 0.00439 -0.0931 0.2364 0.7099 6.000 1.0850 0.01095 0.00461 -0.0922 0.2212 0.7158 6.250 1.1032 0.01142 0.00493 -0.0907 0.1912 0.7215 6.500 1.1224 0.01180 0.00524 -0.0893 0.1748 0.7273 6.750 1.1426 0.01210 0.00553 -0.0881 0.1656 0.7337 7.000 1.1612 0.01239 0.00580 -0.0865 0.1582 0.7400 7.250 1.1797 0.01264 0.00608 -0.0849 0.1528 0.7476 7.750 1.2158 0.01323 0.00670 -0.0817 0.1420 0.7654 8.000 1.2345 0.01349 0.00702 -0.0802 0.1381 0.7756 8.750 1.2868 0.01442 0.00809 -0.0753 0.1244 0.8240 9.000 1.3028 0.01470 0.00847 -0.0735 0.1193 0.8570 9.500 1.3404 0.01543 0.00936 -0.0713 0.1055 1.0000 9.750 1.3555 0.01598 0.00988 -0.0697 0.0984 1.0000 10.000 1.3703 0.01656 0.01043 -0.0680 0.0901 1.0000 10.250 1.3843 0.01720 0.01104 -0.0664 0.0822 1.0000 10.500 1.3947 0.01807 0.01183 -0.0643 0.0694 1.0000 10.750 1.4004 0.01924 0.01289 -0.0617 0.0527 1.0000 11.000 1.4058 0.02049 0.01406 -0.0593 0.0392 1.0000 11.250 1.4167 0.02143 0.01500 -0.0576 0.0342 1.0000 11.500 1.4280 0.02238 0.01595 -0.0560 0.0306 1.0000 11.750 1.4405 0.02327 0.01687 -0.0546 0.0283 1.0000 12.000 1.4509 0.02432 0.01793 -0.0531 0.0256 1.0000 12.250 1.4634 0.02526 0.01890 -0.0518 0.0242 1.0000 12.500 1.4747 0.02630 0.01998 -0.0506 0.0221 1.0000 12.750 1.4839 0.02752 0.02121 -0.0492 0.0199 1.0000 13.000 1.4946 0.02866 0.02238 -0.0480 0.0177 1.0000 13.250 1.5029 0.03002 0.02376 -0.0467 0.0152 1.0000 13.500 1.5100 0.03150 0.02525 -0.0455 0.0124 1.0000 13.750 1.5156 0.03316 0.02692 -0.0442 0.0099 1.0000 14.000 1.5221 0.03479 0.02859 -0.0431 0.0086 1.0000 14.250 1.5282 0.03651 0.03036 -0.0421 0.0077 1.0000 14.500 1.5349 0.03822 0.03214 -0.0412 0.0071 1.0000 14.750 1.5402 0.04011 0.03408 -0.0404 0.0067 1.0000 15.000 1.5446 0.04216 0.03619 -0.0397 0.0063 1.0000 15.250 1.5489 0.04427 0.03837 -0.0390 0.0059 1.0000 15.500 1.5539 0.04636 0.04053 -0.0385 0.0057 1.0000 15.750 1.5578 0.04862 0.04287 -0.0381 0.0055 1.0000 16.000 1.5610 0.05104 0.04536 -0.0379 0.0053 1.0000 16.250 1.5630 0.05366 0.04806 -0.0377 0.0051 1.0000 16.500 1.5639 0.05648 0.05096 -0.0376 0.0049 1.0000 16.750 1.5639 0.05948 0.05405 -0.0377 0.0048 1.0000 17.000 1.5629 0.06271 0.05736 -0.0380 0.0047 1.0000 17.250 1.5596 0.06636 0.06110 -0.0385 0.0045 1.0000 17.500 1.5558 0.07018 0.06502 -0.0392 0.0044 1.0000 17.750 1.5507 0.07430 0.06924 -0.0402 0.0043 1.0000 18.000 1.5449 0.07868 0.07372 -0.0413 0.0042 1.0000 18.250 1.5408 0.08292 0.07807 -0.0426 0.0041 1.0000 18.500 1.5346 0.08759 0.08285 -0.0442 0.0041 1.0000 18.750 1.5267 0.09259 0.08796 -0.0460 0.0041 1.0000 19.000 1.5179 0.09784 0.09333 -0.0481 0.0040 1.0000 19.250 1.5078 0.10341 0.09901 -0.0504 0.0040 1.0000