XFOIL Version 6.96 Calculated polar for: HQ 1.5/12 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 ------ -------- --------- --------- -------- -------- -------- -17.250 -0.8630 0.11775 0.11553 -0.0166 1.0000 0.0044 -17.000 -0.9320 0.10008 0.09769 -0.0261 1.0000 0.0042 -16.750 -1.0182 0.07982 0.07718 -0.0375 1.0000 0.0038 -16.500 -1.0653 0.06680 0.06394 -0.0455 1.0000 0.0039 -16.250 -1.0965 0.05752 0.05447 -0.0516 1.0000 0.0039 -16.000 -1.1195 0.05043 0.04720 -0.0561 1.0000 0.0039 -15.750 -1.1253 0.04636 0.04303 -0.0583 1.0000 0.0039 -15.500 -1.1391 0.04156 0.03806 -0.0608 1.0000 0.0039 -15.250 -1.1421 0.03839 0.03479 -0.0620 1.0000 0.0039 -15.000 -1.1401 0.03597 0.03228 -0.0626 1.0000 0.0042 -14.750 -1.1408 0.03343 0.02961 -0.0631 1.0000 0.0042 -14.500 -1.1423 0.03100 0.02706 -0.0631 1.0000 0.0043 -14.250 -1.1377 0.02929 0.02527 -0.0627 1.0000 0.0043 -14.000 -1.1358 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0.5908 0.6191 0.500 0.2622 0.00597 0.00096 -0.0441 0.5776 0.6301 0.750 0.2901 0.00600 0.00099 -0.0441 0.5651 0.6401 1.000 0.3180 0.00606 0.00102 -0.0441 0.5511 0.6488 1.250 0.3455 0.00614 0.00106 -0.0440 0.5333 0.6572 1.500 0.3728 0.00625 0.00112 -0.0438 0.5127 0.6653 1.750 0.4000 0.00636 0.00118 -0.0437 0.4913 0.6729 2.000 0.4270 0.00652 0.00125 -0.0436 0.4665 0.6786 2.250 0.4535 0.00670 0.00135 -0.0434 0.4380 0.6847 2.500 0.4801 0.00690 0.00145 -0.0431 0.4090 0.6908 2.750 0.5060 0.00714 0.00158 -0.0429 0.3749 0.6969 3.000 0.5312 0.00745 0.00173 -0.0425 0.3310 0.7038 3.250 0.5563 0.00778 0.00191 -0.0421 0.2917 0.7104 3.500 0.5817 0.00806 0.00208 -0.0417 0.2624 0.7178 3.750 0.6072 0.00833 0.00225 -0.0414 0.2377 0.7246 4.000 0.6336 0.00851 0.00239 -0.0412 0.2213 0.7321 4.250 0.6603 0.00866 0.00253 -0.0410 0.2109 0.7389 4.500 0.6869 0.00880 0.00268 -0.0408 0.2014 0.7467 4.750 0.7133 0.00896 0.00283 -0.0406 0.1906 0.7539 5.000 0.7393 0.00915 0.00300 -0.0403 0.1782 0.7621 5.250 0.7648 0.00937 0.00319 -0.0400 0.1621 0.7699 5.500 0.7891 0.00970 0.00343 -0.0395 0.1382 0.7788 5.750 0.8133 0.01001 0.00368 -0.0389 0.1170 0.7878 6.000 0.8368 0.01039 0.00398 -0.0383 0.0959 0.7974 6.250 0.8603 0.01074 0.00428 -0.0376 0.0779 0.8083 6.500 0.8830 0.01113 0.00461 -0.0369 0.0613 0.8201 6.750 0.9068 0.01140 0.00489 -0.0362 0.0528 0.8331 7.000 0.9301 0.01168 0.00518 -0.0355 0.0456 0.8485 7.250 0.9527 0.01193 0.00549 -0.0347 0.0403 0.8686 7.500 0.9741 0.01208 0.00577 -0.0334 0.0370 0.9099 7.750 1.0120 0.01235 0.00612 -0.0359 0.0338 1.0000 8.000 1.0353 0.01270 0.00645 -0.0353 0.0307 1.0000 8.250 1.0587 0.01302 0.00677 -0.0347 0.0281 1.0000 8.500 1.0821 0.01333 0.00710 -0.0341 0.0260 1.0000 8.750 1.1046 0.01370 0.00746 -0.0333 0.0232 1.0000 9.000 1.1268 0.01408 0.00783 -0.0326 0.0208 1.0000 9.250 1.1484 0.01449 0.00823 -0.0317 0.0179 1.0000 9.500 1.1695 0.01491 0.00864 -0.0308 0.0158 1.0000 9.750 1.1901 0.01535 0.00909 -0.0298 0.0134 1.0000 10.000 1.2093 0.01586 0.00960 -0.0286 0.0102 1.0000 10.250 1.2231 0.01672 0.01042 -0.0267 0.0042 1.0000 10.500 1.2403 0.01729 0.01102 -0.0252 0.0038 1.0000 10.750 1.2550 0.01784 0.01162 -0.0232 0.0035 1.0000 11.000 1.2687 0.01840 0.01223 -0.0211 0.0032 1.0000 11.250 1.2814 0.01902 0.01290 -0.0190 0.0030 1.0000 11.500 1.2947 0.01963 0.01356 -0.0170 0.0028 1.0000 11.750 1.3073 0.02030 0.01431 -0.0151 0.0028 1.0000 12.000 1.3197 0.02100 0.01507 -0.0133 0.0026 1.0000 12.250 1.3312 0.02180 0.01592 -0.0115 0.0026 1.0000 12.500 1.3424 0.02263 0.01682 -0.0098 0.0025 1.0000 12.750 1.3525 0.02358 0.01784 -0.0081 0.0024 1.0000 13.000 1.3620 0.02460 0.01894 -0.0065 0.0024 1.0000 13.250 1.3706 0.02574 0.02015 -0.0049 0.0023 1.0000 13.500 1.3792 0.02691 0.02140 -0.0035 0.0023 1.0000 13.750 1.3858 0.02828 0.02285 -0.0021 0.0022 1.0000 14.000 1.3916 0.02979 0.02446 -0.0008 0.0021 1.0000 14.250 1.3971 0.03137 0.02612 0.0003 0.0021 1.0000 14.500 1.4015 0.03312 0.02795 0.0013 0.0021 1.0000 14.750 1.4044 0.03507 0.03000 0.0021 0.0020 1.0000 15.000 1.4066 0.03718 0.03221 0.0028 0.0020 1.0000 15.250 1.4071 0.03953 0.03465 0.0033 0.0020 1.0000 15.500 1.4060 0.04216 0.03739 0.0036 0.0019 1.0000 15.750 1.4010 0.04533 0.04068 0.0036 0.0019 1.0000 16.000 1.3946 0.04884 0.04432 0.0033 0.0018 1.0000 16.250 1.3923 0.05205 0.04763 0.0027 0.0019 1.0000 16.500 1.3814 0.05655 0.05226 0.0015 0.0018 1.0000 16.750 1.3687 0.06163 0.05748 -0.0002 0.0018 1.0000 17.000 1.3614 0.06616 0.06213 -0.0020 0.0018 1.0000 17.250 1.3477 0.07196 0.06806 -0.0045 0.0018 1.0000 17.500 1.3235 0.07991 0.07619 -0.0084 0.0017 1.0000 17.750 1.3108 0.08614 0.08255 -0.0116 0.0018 1.0000 18.000 1.2945 0.09329 0.08983 -0.0153 0.0018 1.0000 18.250 1.2726 0.10179 0.09848 -0.0200 0.0018 1.0000 18.500 1.2470 0.11123 0.10807 -0.0252 0.0018 1.0000 18.750 1.2207 0.12105 0.11804 -0.0307 0.0018 1.0000