XFOIL Version 6.96 Calculated polar for: AS5048 (18%) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -17.000 -0.7696 0.11033 0.10802 -0.0397 1.0000 0.0080 -16.750 -0.8070 0.09867 0.09618 -0.0459 1.0000 0.0080 -16.500 -0.8368 0.08933 0.08666 -0.0506 1.0000 0.0079 -16.250 -0.8618 0.08151 0.07866 -0.0542 1.0000 0.0079 -16.000 -0.8836 0.07478 0.07176 -0.0568 1.0000 0.0079 -15.750 -0.9024 0.06899 0.06580 -0.0586 1.0000 0.0078 -15.500 -0.9193 0.06382 0.06045 -0.0597 1.0000 0.0078 -15.250 -0.9322 0.05952 0.05600 -0.0602 1.0000 0.0079 -15.000 -0.9444 0.05551 0.05182 -0.0602 1.0000 0.0079 -14.750 -0.9441 0.05137 0.04750 -0.0626 0.9989 0.0079 -14.500 -0.9371 0.04758 0.04352 -0.0655 0.9944 0.0079 -14.250 -0.9194 0.04386 0.03958 -0.0700 0.9411 0.0080 -14.000 -0.8620 0.03967 0.03470 -0.0837 0.8368 0.0081 -13.750 -0.8589 0.03821 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0.500 0.3391 0.00770 0.00277 -0.0598 0.6527 0.6603 0.750 0.3687 0.00774 0.00279 -0.0603 0.6489 0.6618 1.000 0.3970 0.00765 0.00273 -0.0604 0.6443 0.6633 1.250 0.4255 0.00759 0.00267 -0.0606 0.6387 0.6647 1.500 0.4545 0.00758 0.00264 -0.0609 0.6346 0.6660 1.750 0.4838 0.00759 0.00265 -0.0613 0.6310 0.6674 2.000 0.5129 0.00757 0.00265 -0.0617 0.6266 0.6686 2.250 0.5419 0.00756 0.00264 -0.0620 0.6212 0.6696 2.500 0.5704 0.00756 0.00261 -0.0622 0.6159 0.6707 2.750 0.5994 0.00749 0.00260 -0.0626 0.6099 0.6723 3.000 0.6277 0.00748 0.00259 -0.0628 0.6026 0.6738 3.250 0.6560 0.00748 0.00261 -0.0630 0.5935 0.6752 3.500 0.6836 0.00751 0.00263 -0.0630 0.5813 0.6766 3.750 0.7108 0.00757 0.00266 -0.0630 0.5662 0.6778 4.000 0.7372 0.00768 0.00272 -0.0628 0.5458 0.6791 4.250 0.7617 0.00789 0.00282 -0.0623 0.5174 0.6804 4.500 0.7848 0.00819 0.00298 -0.0615 0.4826 0.6818 4.750 0.8073 0.00855 0.00319 -0.0607 0.4472 0.6833 5.000 0.8300 0.00889 0.00341 -0.0599 0.4155 0.6846 5.250 0.8525 0.00925 0.00363 -0.0590 0.3865 0.6858 5.500 0.8751 0.00959 0.00386 -0.0582 0.3587 0.6867 5.750 0.8977 0.00990 0.00408 -0.0575 0.3353 0.6880 6.000 0.9198 0.01019 0.00429 -0.0566 0.3112 0.6898 6.250 0.9409 0.01055 0.00455 -0.0556 0.2868 0.6913 6.500 0.9619 0.01091 0.00482 -0.0545 0.2624 0.6927 6.750 0.9825 0.01129 0.00511 -0.0534 0.2417 0.6942 7.000 1.0029 0.01165 0.00540 -0.0523 0.2235 0.6958 7.250 1.0235 0.01200 0.00569 -0.0512 0.2079 0.6974 7.500 1.0441 0.01233 0.00598 -0.0501 0.1947 0.6989 7.750 1.0650 0.01264 0.00626 -0.0490 0.1840 0.7003 8.000 1.0839 0.01298 0.00657 -0.0476 0.1741 0.7017 8.250 1.1011 0.01328 0.00685 -0.0458 0.1657 0.7029 8.500 1.1190 0.01361 0.00716 -0.0442 0.1583 0.7040 8.750 1.1377 0.01394 0.00750 -0.0429 0.1508 0.7060 9.000 1.1565 0.01430 0.00787 -0.0416 0.1434 0.7079 9.250 1.1750 0.01469 0.00826 -0.0403 0.1363 0.7097 9.500 1.1928 0.01511 0.00869 -0.0389 0.1294 0.7116 9.750 1.2099 0.01558 0.00914 -0.0375 0.1217 0.7134 10.000 1.2265 0.01607 0.00964 -0.0360 0.1147 0.7153 10.250 1.2414 0.01666 0.01020 -0.0343 0.1066 0.7171 10.500 1.2569 0.01724 0.01078 -0.0329 0.0994 0.7188 10.750 1.2698 0.01798 0.01149 -0.0312 0.0918 0.7203 11.000 1.2841 0.01868 0.01220 -0.0298 0.0858 0.7222 11.250 1.2966 0.01952 0.01304 -0.0283 0.0794 0.7246 11.500 1.3097 0.02039 0.01393 -0.0271 0.0744 0.7268 11.750 1.3218 0.02140 0.01496 -0.0259 0.0691 0.7291 12.000 1.3352 0.02237 0.01597 -0.0250 0.0650 0.7313 12.250 1.3457 0.02362 0.01721 -0.0239 0.0601 0.7335 12.500 1.3600 0.02462 0.01826 -0.0233 0.0573 0.7357 12.750 1.3708 0.02589 0.01953 -0.0224 0.0538 0.7377 13.000 1.3822 0.02713 0.02082 -0.0217 0.0508 0.7410 13.250 1.3946 0.02830 0.02205 -0.0210 0.0485 0.7443 13.500 1.4042 0.02969 0.02347 -0.0202 0.0460 0.7476 13.750 1.4123 0.03119 0.02500 -0.0193 0.0436 0.7509 14.000 1.4239 0.03242 0.02631 -0.0187 0.0422 0.7541 14.250 1.4334 0.03383 0.02777 -0.0180 0.0404 0.7583 14.500 1.4398 0.03550 0.02948 -0.0171 0.0385 0.7631 14.750 1.4458 0.03720 0.03126 -0.0163 0.0368 0.7683 15.000 1.4558 0.03861 0.03276 -0.0158 0.0358 0.7749 15.250 1.4636 0.04023 0.03447 -0.0152 0.0345 0.7840 15.500 1.4695 0.04206 0.03639 -0.0147 0.0332 0.7975 15.750 1.4726 0.04420 0.03868 -0.0142 0.0318 0.8260 16.000 1.4527 0.04523 0.04009 -0.0077 0.0312 0.9895 16.250 1.4595 0.04688 0.04181 -0.0072 0.0304 1.0000 16.500 1.4658 0.04883 0.04383 -0.0069 0.0296 1.0000 16.750 1.4700 0.05105 0.04609 -0.0067 0.0285 1.0000 17.000 1.4717 0.05356 0.04863 -0.0066 0.0274 1.0000 17.250 1.4693 0.05655 0.05168 -0.0064 0.0262 1.0000 17.500 1.4751 0.05874 0.05395 -0.0065 0.0256 1.0000 17.750 1.4785 0.06123 0.05651 -0.0066 0.0248 1.0000 18.000 1.4795 0.06404 0.05938 -0.0068 0.0240 1.0000 18.250 1.4777 0.06721 0.06261 -0.0072 0.0233 1.0000 18.500 1.4726 0.07085 0.06632 -0.0076 0.0226 1.0000 18.750 1.4629 0.07517 0.07072 -0.0084 0.0220 1.0000 19.000 1.4626 0.07837 0.07401 -0.0090 0.0216 1.0000 19.250 1.4598 0.08194 0.07768 -0.0099 0.0212 1.0000