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 = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -14.250 -0.6439 0.08302 0.08094 -0.0617 1.0000 0.0054 -14.000 -0.7365 0.06114 0.05880 -0.0742 1.0000 0.0051 -13.750 -0.7677 0.05022 0.04769 -0.0820 1.0000 0.0050 -13.500 -0.7894 0.04347 0.04079 -0.0868 1.0000 0.0050 -13.250 -0.8038 0.03810 0.03525 -0.0910 0.9991 0.0050 -13.000 -0.8111 0.03203 0.02892 -0.0984 0.9842 0.0051 -12.750 -0.7957 0.02859 0.02527 -0.1043 0.9754 0.0051 -12.500 -0.7779 0.02567 0.02213 -0.1092 0.9635 0.0052 -12.250 -0.7580 0.02394 0.02022 -0.1111 0.9509 0.0053 -12.000 -0.7425 0.02246 0.01857 -0.1113 0.9350 0.0054 -11.750 -0.7269 0.02138 0.01734 -0.1107 0.9213 0.0054 -11.500 -0.7111 0.02040 0.01620 -0.1099 0.9100 0.0055 -11.250 -0.6936 0.01955 0.01521 -0.1090 0.9002 0.0056 -11.000 -0.6749 0.01874 0.01428 -0.1083 0.8916 0.0057 -10.500 -0.6346 0.01726 0.01256 -0.1070 0.8767 0.0059 -10.250 -0.6133 0.01659 0.01177 -0.1064 0.8696 0.0060 -10.000 -0.5906 0.01600 0.01110 -0.1060 0.8632 0.0061 -9.750 -0.5675 0.01547 0.01046 -0.1055 0.8568 0.0063 -9.500 -0.5440 0.01493 0.00983 -0.1052 0.8511 0.0065 -9.250 -0.5201 0.01439 0.00919 -0.1048 0.8449 0.0066 -8.750 -0.4711 0.01341 0.00804 -0.1042 0.8335 0.0068 -8.500 -0.4460 0.01299 0.00754 -0.1039 0.8276 0.0070 -8.250 -0.4205 0.01261 0.00708 -0.1036 0.8221 0.0070 -8.000 -0.3949 0.01219 0.00659 -0.1034 0.8161 0.0071 -7.750 -0.3697 0.01172 0.00604 -0.1032 0.8104 0.0074 -7.500 -0.3437 0.01134 0.00560 -0.1030 0.8049 0.0076 -7.250 -0.3174 0.01101 0.00521 -0.1028 0.7989 0.0078 -7.000 -0.2910 0.01072 0.00486 -0.1027 0.7934 0.0081 -6.750 -0.2641 0.01043 0.00452 -0.1026 0.7879 0.0083 -6.500 -0.2373 0.01019 0.00423 -0.1025 0.7820 0.0086 -6.250 -0.2102 0.00996 0.00395 -0.1024 0.7767 0.0089 -6.000 -0.1829 0.00974 0.00369 -0.1023 0.7711 0.0093 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0.4221 0.00633 0.00118 -0.1023 0.6171 0.5209 -0.250 0.4495 0.00628 0.00122 -0.1022 0.6072 0.5661 0.000 0.4768 0.00630 0.00126 -0.1021 0.5964 0.5966 0.250 0.5040 0.00636 0.00130 -0.1020 0.5823 0.6102 0.500 0.5311 0.00644 0.00134 -0.1018 0.5678 0.6202 0.750 0.5583 0.00653 0.00139 -0.1017 0.5546 0.6300 1.000 0.5853 0.00663 0.00144 -0.1015 0.5401 0.6379 1.250 0.6122 0.00675 0.00150 -0.1013 0.5234 0.6433 1.500 0.6383 0.00690 0.00158 -0.1010 0.5026 0.6484 1.750 0.6639 0.00711 0.00168 -0.1006 0.4783 0.6537 2.000 0.6894 0.00732 0.00179 -0.1002 0.4544 0.6587 2.250 0.7149 0.00751 0.00191 -0.0998 0.4333 0.6641 2.500 0.7403 0.00772 0.00203 -0.0994 0.4115 0.6695 2.750 0.7653 0.00796 0.00217 -0.0990 0.3883 0.6747 3.000 0.7898 0.00822 0.00233 -0.0984 0.3636 0.6804 3.250 0.8143 0.00848 0.00250 -0.0979 0.3382 0.6864 3.500 0.8378 0.00879 0.00269 -0.0972 0.3094 0.6919 3.750 0.8616 0.00908 0.00288 -0.0966 0.2885 0.6982 4.250 0.9111 0.00950 0.00324 -0.0956 0.2633 0.7104 4.500 0.9362 0.00969 0.00340 -0.0952 0.2554 0.7171 4.750 0.9612 0.00986 0.00358 -0.0947 0.2479 0.7234 5.000 0.9861 0.01004 0.00375 -0.0943 0.2416 0.7303 5.250 1.0112 0.01019 0.00392 -0.0939 0.2364 0.7372 5.500 1.0354 0.01039 0.00412 -0.0933 0.2300 0.7446 5.750 1.0603 0.01054 0.00430 -0.0929 0.2252 0.7520 6.000 1.0842 0.01073 0.00450 -0.0923 0.2185 0.7603 6.250 1.1078 0.01093 0.00470 -0.0916 0.2113 0.7686 6.500 1.1310 0.01114 0.00492 -0.0909 0.2038 0.7779 6.750 1.1534 0.01137 0.00515 -0.0900 0.1939 0.7878 7.000 1.1751 0.01162 0.00540 -0.0890 0.1854 0.7987 7.250 1.1971 0.01182 0.00564 -0.0881 0.1774 0.8113 7.500 1.2171 0.01209 0.00592 -0.0868 0.1667 0.8279 8.000 1.2556 0.01256 0.00656 -0.0841 0.1404 1.0000 8.250 1.2711 0.01300 0.00694 -0.0821 0.1274 1.0000 8.500 1.2845 0.01355 0.00740 -0.0797 0.1109 1.0000 8.750 1.2983 0.01411 0.00788 -0.0776 0.0972 1.0000 9.000 1.3085 0.01486 0.00850 -0.0749 0.0779 1.0000 9.250 1.3198 0.01558 0.00913 -0.0725 0.0624 1.0000 9.500 1.3316 0.01631 0.00979 -0.0703 0.0502 1.0000 9.750 1.3430 0.01708 0.01049 -0.0681 0.0390 1.0000 10.000 1.3532 0.01794 0.01129 -0.0658 0.0281 1.0000 10.250 1.3620 0.01892 0.01221 -0.0635 0.0176 1.0000 10.500 1.3714 0.01990 0.01317 -0.0613 0.0104 1.0000 10.750 1.3807 0.02092 0.01418 -0.0592 0.0048 1.0000 11.000 1.3928 0.02178 0.01506 -0.0575 0.0041 1.0000 11.250 1.4055 0.02262 0.01594 -0.0560 0.0036 1.0000 11.500 1.4187 0.02344 0.01681 -0.0546 0.0035 1.0000 11.750 1.4304 0.02439 0.01781 -0.0531 0.0032 1.0000 12.000 1.4427 0.02533 0.01880 -0.0518 0.0032 1.0000 12.250 1.4528 0.02644 0.01997 -0.0503 0.0029 1.0000 12.500 1.4629 0.02758 0.02118 -0.0489 0.0028 1.0000 12.750 1.4723 0.02880 0.02246 -0.0476 0.0027 1.0000 13.000 1.4804 0.03017 0.02389 -0.0462 0.0026 1.0000 13.250 1.4856 0.03182 0.02563 -0.0448 0.0024 1.0000 13.500 1.4935 0.03327 0.02714 -0.0436 0.0023 1.0000 13.750 1.5012 0.03479 0.02872 -0.0426 0.0023 1.0000 14.000 1.5074 0.03649 0.03051 -0.0415 0.0022 1.0000 14.250 1.5132 0.03826 0.03235 -0.0406 0.0022 1.0000 14.500 1.5177 0.04023 0.03440 -0.0398 0.0021 1.0000 14.750 1.5216 0.04233 0.03658 -0.0390 0.0021 1.0000 15.000 1.5254 0.04450 0.03883 -0.0385 0.0021 1.0000 15.250 1.5269 0.04699 0.04141 -0.0379 0.0020 1.0000 15.500 1.5285 0.04958 0.04408 -0.0376 0.0020 1.0000 15.750 1.5282 0.05246 0.04707 -0.0374 0.0019 1.0000 16.000 1.5275 0.05550 0.05019 -0.0374 0.0019 1.0000 16.250 1.5251 0.05885 0.05365 -0.0376 0.0019 1.0000 16.500 1.5221 0.06241 0.05730 -0.0380 0.0018 1.0000 16.750 1.5174 0.06633 0.06135 -0.0387 0.0018 1.0000 17.000 1.5125 0.07042 0.06554 -0.0396 0.0018 1.0000 17.250 1.5053 0.07498 0.07021 -0.0408 0.0018 1.0000 17.500 1.4968 0.07991 0.07526 -0.0423 0.0018 1.0000 17.750 1.4864 0.08534 0.08082 -0.0442 0.0017 1.0000 18.000 1.4768 0.09077 0.08637 -0.0463 0.0017 1.0000 18.250 1.4633 0.09705 0.09278 -0.0488 0.0017 1.0000 18.500 1.4503 0.10341 0.09926 -0.0516 0.0017 1.0000 18.750 1.4353 0.11029 0.10628 -0.0548 0.0017 1.0000 19.000 1.4211 0.11710 0.11322 -0.0582 0.0017 1.0000