XFOIL Version 6.96 Calculated polar for: HQ 3.0/11 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 ------ -------- --------- --------- -------- -------- -------- -10.250 -0.3976 0.09247 0.09020 -0.0421 1.0000 0.0061 -10.000 -0.4040 0.08748 0.08525 -0.0440 1.0000 0.0060 -9.500 -0.5581 0.03168 0.02858 -0.0900 0.9606 0.0055 -9.250 -0.5461 0.02707 0.02344 -0.0921 0.9492 0.0057 -9.000 -0.5277 0.02437 0.02035 -0.0928 0.9400 0.0059 -8.750 -0.5082 0.02226 0.01788 -0.0929 0.9310 0.0061 -8.500 -0.4876 0.02062 0.01594 -0.0927 0.9230 0.0063 -8.250 -0.4653 0.01922 0.01427 -0.0925 0.9160 0.0066 -8.000 -0.4420 0.01829 0.01313 -0.0921 0.9090 0.0069 -7.750 -0.4182 0.01737 0.01200 -0.0918 0.9028 0.0072 -7.500 -0.3964 0.01603 0.01047 -0.0913 0.8963 0.0077 -7.250 -0.3721 0.01526 0.00958 -0.0910 0.8901 0.0080 -7.000 -0.3474 0.01455 0.00875 -0.0907 0.8844 0.0083 -6.750 -0.3223 0.01392 0.00799 -0.0903 0.8782 0.0087 -6.250 -0.2713 0.01280 0.00665 -0.0898 0.8668 0.0094 -6.000 -0.2454 0.01233 0.00607 -0.0895 0.8611 0.0098 -5.750 -0.2191 0.01192 0.00556 -0.0893 0.8557 0.0103 -5.500 -0.1931 0.01143 0.00500 -0.0891 0.8497 0.0112 -5.250 -0.1665 0.01105 0.00454 -0.0889 0.8444 0.0123 -5.000 -0.1397 0.01072 0.00415 -0.0887 0.8384 0.0133 -4.750 -0.1127 0.01042 0.00379 -0.0886 0.8326 0.0151 -4.500 -0.0858 0.01011 0.00350 -0.0884 0.8270 0.0219 -4.250 -0.0584 0.00992 0.00328 -0.0884 0.8209 0.0289 -4.000 -0.0311 0.00972 0.00306 -0.0883 0.8155 0.0349 -3.750 -0.0035 0.00957 0.00288 -0.0883 0.8091 0.0393 -3.500 0.0239 0.00938 0.00269 -0.0882 0.8031 0.0467 -3.250 0.0515 0.00923 0.00252 -0.0882 0.7968 0.0554 -3.000 0.0789 0.00905 0.00235 -0.0881 0.7901 0.0677 -2.750 0.1064 0.00887 0.00219 -0.0881 0.7832 0.0841 -2.500 0.1337 0.00868 0.00203 -0.0881 0.7755 0.1085 -2.250 0.1609 0.00842 0.00189 -0.0880 0.7676 0.1542 -2.000 0.1877 0.00810 0.00175 -0.0880 0.7600 0.2266 -1.750 0.2145 0.00772 0.00162 -0.0881 0.7528 0.3171 -1.500 0.2405 0.00724 0.00156 -0.0881 0.7459 0.4609 -1.250 0.2678 0.00712 0.00156 -0.0880 0.7391 0.5199 -1.000 0.2954 0.00708 0.00156 -0.0878 0.7316 0.5526 -0.750 0.3228 0.00705 0.00156 -0.0877 0.7219 0.5845 -0.500 0.3496 0.00702 0.00158 -0.0874 0.7108 0.6176 -0.250 0.3768 0.00703 0.00157 -0.0872 0.6997 0.6361 0.000 0.4041 0.00705 0.00157 -0.0870 0.6893 0.6491 0.250 0.4318 0.00706 0.00158 -0.0869 0.6803 0.6592 0.500 0.4593 0.00710 0.00158 -0.0868 0.6711 0.6677 0.750 0.4868 0.00713 0.00160 -0.0867 0.6610 0.6754 1.000 0.5142 0.00717 0.00163 -0.0866 0.6500 0.6840 1.250 0.5412 0.00722 0.00166 -0.0864 0.6365 0.6935 1.500 0.5677 0.00728 0.00169 -0.0861 0.6195 0.7040 1.750 0.5941 0.00736 0.00175 -0.0858 0.6026 0.7165 2.000 0.6203 0.00742 0.00182 -0.0854 0.5856 0.7312 2.250 0.6459 0.00750 0.00190 -0.0849 0.5659 0.7500 2.500 0.6707 0.00761 0.00202 -0.0843 0.5449 0.7745 2.750 0.6950 0.00775 0.00216 -0.0835 0.5206 0.8036 3.000 0.7186 0.00794 0.00230 -0.0827 0.4927 0.8321 3.250 0.7422 0.00818 0.00246 -0.0819 0.4641 0.8541 3.500 0.7656 0.00842 0.00262 -0.0810 0.4359 0.8719 3.750 0.7886 0.00866 0.00280 -0.0801 0.4087 0.8892 4.000 0.8111 0.00887 0.00297 -0.0791 0.3821 0.9120 4.250 0.8441 0.00912 0.00317 -0.0804 0.3524 1.0000 4.500 0.8682 0.00947 0.00340 -0.0799 0.3250 1.0000 5.000 0.9165 0.01015 0.00390 -0.0789 0.2820 1.0000 5.250 0.9407 0.01048 0.00416 -0.0784 0.2641 1.0000 5.500 0.9646 0.01083 0.00443 -0.0779 0.2464 1.0000 5.750 0.9884 0.01117 0.00472 -0.0773 0.2290 1.0000 6.000 1.0112 0.01158 0.00503 -0.0767 0.2051 1.0000 6.250 1.0328 0.01208 0.00538 -0.0758 0.1774 1.0000 6.500 1.0544 0.01258 0.00575 -0.0750 0.1538 1.0000 6.750 1.0757 0.01307 0.00615 -0.0741 0.1332 1.0000 7.000 1.0963 0.01362 0.00657 -0.0731 0.1097 1.0000 7.250 1.1165 0.01418 0.00701 -0.0721 0.0893 1.0000 7.500 1.1371 0.01469 0.00746 -0.0711 0.0747 1.0000 7.750 1.1568 0.01525 0.00795 -0.0700 0.0605 1.0000 8.000 1.1756 0.01585 0.00848 -0.0687 0.0475 1.0000 8.250 1.1929 0.01654 0.00910 -0.0672 0.0336 1.0000 8.500 1.2103 0.01718 0.00969 -0.0658 0.0242 1.0000 8.750 1.2248 0.01791 0.01036 -0.0638 0.0145 1.0000 9.000 1.2371 0.01872 0.01113 -0.0615 0.0057 1.0000 9.250 1.2511 0.01942 0.01185 -0.0595 0.0047 1.0000 9.500 1.2657 0.02008 0.01256 -0.0576 0.0040 1.0000 9.750 1.2806 0.02072 0.01328 -0.0559 0.0039 1.0000 10.000 1.2945 0.02144 0.01411 -0.0540 0.0037 1.0000 10.250 1.3076 0.02223 0.01499 -0.0522 0.0035 1.0000 10.500 1.3199 0.02308 0.01593 -0.0504 0.0033 1.0000 10.750 1.3312 0.02403 0.01698 -0.0485 0.0032 1.0000 11.000 1.3415 0.02508 0.01813 -0.0466 0.0031 1.0000 11.250 1.3505 0.02624 0.01940 -0.0447 0.0030 1.0000 11.500 1.3592 0.02747 0.02073 -0.0429 0.0029 1.0000 11.750 1.3659 0.02888 0.02225 -0.0411 0.0028 1.0000 12.000 1.3697 0.03058 0.02408 -0.0392 0.0027 1.0000 12.250 1.3731 0.03236 0.02598 -0.0374 0.0027 1.0000 12.500 1.3746 0.03438 0.02814 -0.0358 0.0026 1.0000 12.750 1.3746 0.03662 0.03051 -0.0343 0.0026 1.0000 13.000 1.3762 0.03881 0.03281 -0.0331 0.0025 1.0000 13.250 1.3803 0.04083 0.03495 -0.0323 0.0025 1.0000 13.500 1.3823 0.04315 0.03739 -0.0316 0.0024 1.0000 13.750 1.3837 0.04564 0.03999 -0.0311 0.0024 1.0000 14.000 1.3815 0.04862 0.04310 -0.0307 0.0023 1.0000 14.250 1.3783 0.05187 0.04649 -0.0307 0.0023 1.0000 14.500 1.3746 0.05536 0.05011 -0.0310 0.0023 1.0000 14.750 1.3696 0.05921 0.05410 -0.0315 0.0022 1.0000 15.000 1.3628 0.06352 0.05855 -0.0325 0.0022 1.0000 15.250 1.3541 0.06837 0.06355 -0.0340 0.0022 1.0000 15.500 1.3457 0.07342 0.06874 -0.0357 0.0022 1.0000 15.750 1.3353 0.07906 0.07453 -0.0380 0.0022 1.0000 16.000 1.3263 0.08471 0.08032 -0.0405 0.0021 1.0000 16.250 1.3123 0.09146 0.08722 -0.0436 0.0021 1.0000 16.500 1.3007 0.09803 0.09393 -0.0468 0.0021 1.0000 16.750 1.2872 0.10512 0.10118 -0.0504 0.0021 1.0000 17.000 1.2738 0.11239 0.10858 -0.0541 0.0021 1.0000