XFOIL Version 6.96 Calculated polar for: HQ 3.0/14 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 -0.7330 0.10517 0.10279 -0.0488 1.0000 0.0060 -16.500 -0.8116 0.08685 0.08428 -0.0589 1.0000 0.0059 -16.250 -0.9056 0.06572 0.06283 -0.0715 1.0000 0.0057 -16.000 -0.9399 0.05580 0.05272 -0.0782 1.0000 0.0056 -15.750 -0.9617 0.04911 0.04586 -0.0826 1.0000 0.0056 -15.500 -0.9763 0.04405 0.04066 -0.0856 1.0000 0.0056 -15.250 -0.9853 0.04010 0.03660 -0.0875 1.0000 0.0056 -15.000 -0.9917 0.03674 0.03312 -0.0888 1.0000 0.0057 -14.750 -0.9941 0.03406 0.03034 -0.0895 1.0000 0.0057 -14.500 -0.9951 0.03174 0.02793 -0.0897 1.0000 0.0058 -14.250 -0.9965 0.02962 0.02572 -0.0894 1.0000 0.0058 -14.000 -0.9974 0.02786 0.02387 -0.0885 1.0000 0.0059 -13.750 -0.9887 0.02612 0.02202 -0.0891 0.9913 0.0060 -13.500 -0.9668 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1.250 0.5459 0.00671 0.00146 -0.0866 0.5337 0.6180 1.500 0.5726 0.00682 0.00153 -0.0864 0.5170 0.6259 1.750 0.5991 0.00697 0.00160 -0.0861 0.4994 0.6317 2.000 0.6253 0.00711 0.00169 -0.0859 0.4815 0.6371 2.250 0.6517 0.00725 0.00178 -0.0856 0.4652 0.6428 2.500 0.6777 0.00743 0.00188 -0.0853 0.4467 0.6479 2.750 0.7031 0.00762 0.00200 -0.0849 0.4258 0.6530 3.000 0.7285 0.00782 0.00214 -0.0845 0.4067 0.6587 3.500 0.7787 0.00824 0.00242 -0.0836 0.3657 0.6702 3.750 0.8028 0.00850 0.00259 -0.0830 0.3421 0.6763 4.000 0.8270 0.00876 0.00276 -0.0824 0.3195 0.6820 4.250 0.8513 0.00899 0.00294 -0.0818 0.3028 0.6886 4.500 0.8757 0.00922 0.00312 -0.0812 0.2874 0.6950 4.750 0.8998 0.00944 0.00331 -0.0807 0.2734 0.7014 5.000 0.9244 0.00964 0.00349 -0.0801 0.2629 0.7086 5.250 0.9484 0.00986 0.00368 -0.0795 0.2519 0.7153 5.500 0.9720 0.01009 0.00389 -0.0789 0.2394 0.7228 5.750 0.9962 0.01028 0.00407 -0.0783 0.2299 0.7297 6.000 1.0194 0.01052 0.00429 -0.0775 0.2188 0.7376 6.250 1.0417 0.01078 0.00453 -0.0766 0.2060 0.7455 6.500 1.0636 0.01106 0.00477 -0.0757 0.1943 0.7539 6.750 1.0853 0.01133 0.00502 -0.0747 0.1829 0.7618 7.000 1.1047 0.01169 0.00533 -0.0733 0.1672 0.7713 7.250 1.1254 0.01196 0.00560 -0.0722 0.1577 0.7807 7.500 1.1436 0.01229 0.00590 -0.0706 0.1451 0.7909 7.750 1.1604 0.01259 0.00619 -0.0687 0.1365 0.8023 8.000 1.1783 0.01283 0.00648 -0.0670 0.1302 0.8158 8.250 1.1932 0.01319 0.00683 -0.0648 0.1199 0.8327 8.500 1.2058 0.01359 0.00724 -0.0622 0.1070 0.8576 9.000 1.2435 0.01442 0.00817 -0.0600 0.0845 1.0000 9.250 1.2587 0.01492 0.00864 -0.0582 0.0760 1.0000 9.500 1.2733 0.01545 0.00914 -0.0564 0.0683 1.0000 9.750 1.2865 0.01608 0.00972 -0.0544 0.0598 1.0000 10.000 1.2986 0.01678 0.01038 -0.0524 0.0510 1.0000 10.250 1.3120 0.01745 0.01101 -0.0506 0.0445 1.0000 10.500 1.3244 0.01818 0.01173 -0.0488 0.0384 1.0000 10.750 1.3349 0.01905 0.01256 -0.0468 0.0313 1.0000 11.000 1.3474 0.01983 0.01333 -0.0451 0.0278 1.0000 11.250 1.3586 0.02072 0.01422 -0.0434 0.0226 1.0000 11.500 1.3687 0.02171 0.01519 -0.0417 0.0179 1.0000 11.750 1.3785 0.02275 0.01622 -0.0400 0.0142 1.0000 12.000 1.3890 0.02377 0.01726 -0.0385 0.0114 1.0000 12.250 1.3900 0.02550 0.01897 -0.0362 0.0041 1.0000 12.500 1.4003 0.02661 0.02012 -0.0348 0.0038 1.0000 12.750 1.4095 0.02784 0.02140 -0.0335 0.0034 1.0000 13.000 1.4194 0.02904 0.02265 -0.0323 0.0033 1.0000 13.250 1.4284 0.03034 0.02401 -0.0312 0.0031 1.0000 13.500 1.4378 0.03164 0.02537 -0.0301 0.0030 1.0000 13.750 1.4459 0.03308 0.02688 -0.0291 0.0029 1.0000 14.000 1.4537 0.03458 0.02844 -0.0281 0.0028 1.0000 14.250 1.4608 0.03619 0.03012 -0.0273 0.0028 1.0000 14.500 1.4674 0.03790 0.03189 -0.0265 0.0027 1.0000 14.750 1.4735 0.03970 0.03376 -0.0257 0.0027 1.0000 15.000 1.4784 0.04167 0.03581 -0.0251 0.0026 1.0000 15.250 1.4818 0.04386 0.03807 -0.0246 0.0025 1.0000 15.500 1.4843 0.04622 0.04051 -0.0241 0.0024 1.0000 15.750 1.4880 0.04851 0.04288 -0.0238 0.0024 1.0000 16.000 1.4878 0.05131 0.04577 -0.0237 0.0023 1.0000 16.250 1.4875 0.05422 0.04877 -0.0237 0.0022 1.0000 16.500 1.4845 0.05757 0.05222 -0.0238 0.0022 1.0000 16.750 1.4819 0.06095 0.05570 -0.0242 0.0021 1.0000 17.000 1.4775 0.06471 0.05957 -0.0248 0.0021 1.0000 17.250 1.4720 0.06875 0.06371 -0.0257 0.0021 1.0000 17.500 1.4673 0.07280 0.06786 -0.0267 0.0020 1.0000 17.750 1.4610 0.07720 0.07237 -0.0280 0.0020 1.0000 18.000 1.4547 0.08174 0.07702 -0.0294 0.0020 1.0000 18.250 1.4469 0.08663 0.08202 -0.0312 0.0020 1.0000 18.500 1.4369 0.09202 0.08753 -0.0333 0.0020 1.0000 18.750 1.4272 0.09746 0.09308 -0.0356 0.0020 1.0000 19.000 1.4166 0.10319 0.09892 -0.0381 0.0020 1.0000 19.250 1.4031 0.10958 0.10544 -0.0411 0.0019 1.0000