XFOIL Version 6.96 Calculated polar for: NACA 16-021 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -1.0989 0.08207 0.07706 -0.0873 0.9955 0.0261 -19.500 -1.0998 0.07890 0.07381 -0.0879 0.9950 0.0266 -19.250 -1.0958 0.07620 0.07106 -0.0889 0.9945 0.0270 -19.000 -1.0913 0.07354 0.06835 -0.0900 0.9940 0.0275 -18.750 -1.0868 0.07089 0.06563 -0.0910 0.9935 0.0279 -18.500 -1.0859 0.06835 0.06299 -0.0908 0.9922 0.0283 -18.250 -1.0841 0.06588 0.06042 -0.0907 0.9909 0.0287 -18.000 -1.0811 0.06352 0.05795 -0.0906 0.9897 0.0292 -17.750 -1.0763 0.06131 0.05562 -0.0907 0.9885 0.0297 -17.500 -1.0702 0.05914 0.05331 -0.0908 0.9874 0.0301 -17.250 -1.0631 0.05703 0.05104 -0.0911 0.9864 0.0305 -17.000 -1.0531 0.05527 0.04925 -0.0910 0.9858 0.0313 -16.750 -1.0420 0.05361 0.04757 -0.0912 0.9851 0.0319 -16.500 -1.0304 0.05203 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3.250 0.5097 0.01527 0.01100 -0.0357 0.8155 0.8657 3.500 0.5138 0.01506 0.01080 -0.0306 0.8080 0.8696 3.750 0.5501 0.01498 0.01074 -0.0326 0.8013 0.8701 4.000 0.5632 0.01511 0.01090 -0.0293 0.7911 0.8716 4.250 0.5740 0.01520 0.01101 -0.0255 0.7778 0.8735 4.500 0.5824 0.01517 0.01096 -0.0213 0.7626 0.8768 4.750 0.5581 0.01481 0.01057 -0.0101 0.7512 0.8856 5.000 0.5767 0.01496 0.01071 -0.0081 0.7305 0.8868 5.250 0.5975 0.01511 0.01079 -0.0068 0.7039 0.8881 5.500 0.6061 0.01540 0.01095 -0.0027 0.6671 0.8906 5.750 0.5689 0.01517 0.01064 0.0112 0.6467 0.9007 6.000 0.5693 0.01594 0.01114 0.0168 0.5872 0.9025 6.250 0.5602 0.01693 0.01184 0.0241 0.5247 0.9052 7.000 0.4796 0.01777 0.01226 0.0577 0.4274 0.9288 7.250 0.4891 0.01897 0.01314 0.0601 0.3580 0.9296 7.500 0.5022 0.02004 0.01392 0.0616 0.2968 0.9303 7.750 0.5179 0.02098 0.01461 0.0627 0.2442 0.9311 8.000 0.5347 0.02183 0.01526 0.0637 0.2020 0.9320 8.250 0.5538 0.02258 0.01585 0.0642 0.1700 0.9330 8.500 0.5743 0.02325 0.01641 0.0645 0.1458 0.9342 8.750 0.5933 0.02388 0.01695 0.0652 0.1264 0.9358 9.000 0.5724 0.02384 0.01688 0.0748 0.1204 0.9443 9.250 0.5960 0.02448 0.01746 0.0744 0.1045 0.9449 9.500 0.6189 0.02514 0.01806 0.0741 0.0907 0.9455 9.750 0.6412 0.02585 0.01872 0.0738 0.0796 0.9463 10.000 0.6626 0.02663 0.01944 0.0737 0.0712 0.9471 10.250 0.6845 0.02728 0.02009 0.0736 0.0655 0.9481 10.500 0.7026 0.02802 0.02082 0.0742 0.0613 0.9495 10.750 0.7196 0.02858 0.02142 0.0751 0.0582 0.9513 11.000 0.7086 0.02883 0.02167 0.0822 0.0568 0.9581 11.250 0.7289 0.02974 0.02259 0.0820 0.0539 0.9587 11.500 0.7522 0.03044 0.02334 0.0814 0.0519 0.9593 11.750 0.7737 0.03122 0.02415 0.0810 0.0501 0.9600 12.000 0.7914 0.03217 0.02509 0.0812 0.0484 0.9608 12.250 0.8072 0.03317 0.02613 0.0817 0.0469 0.9617 12.500 0.8262 0.03391 0.02693 0.0818 0.0457 0.9629 12.750 0.8420 0.03471 0.02779 0.0825 0.0445 0.9645 13.000 0.8524 0.03550 0.02861 0.0843 0.0435 0.9672 13.250 0.8554 0.03623 0.02936 0.0877 0.0428 0.9712 13.500 0.8711 0.03741 0.03055 0.0878 0.0416 0.9717 13.750 0.8875 0.03853 0.03173 0.0878 0.0406 0.9722 14.000 0.9067 0.03945 0.03273 0.0875 0.0398 0.9729 14.250 0.9239 0.04048 0.03383 0.0874 0.0389 0.9736 14.500 0.9400 0.04155 0.03495 0.0874 0.0380 0.9745 14.750 0.9551 0.04265 0.03609 0.0875 0.0372 0.9755 15.000 0.9682 0.04388 0.03734 0.0878 0.0364 0.9768 15.250 0.9791 0.04528 0.03875 0.0886 0.0354 0.9781 15.500 0.9870 0.04642 0.03998 0.0902 0.0350 0.9808 15.750 0.9935 0.04761 0.04126 0.0919 0.0345 0.9830 16.000 1.0079 0.04897 0.04273 0.0916 0.0338 0.9835 16.250 1.0213 0.05042 0.04426 0.0912 0.0331 0.9840 16.500 1.0338 0.05194 0.04584 0.0909 0.0325 0.9846 16.750 1.0454 0.05350 0.04745 0.0906 0.0318 0.9853 17.000 1.0564 0.05516 0.04913 0.0904 0.0312 0.9860 17.250 1.0665 0.05692 0.05094 0.0906 0.0305 0.9866 17.500 1.0735 0.05903 0.05320 0.0903 0.0301 0.9877 17.750 1.0797 0.06120 0.05550 0.0902 0.0296 0.9888 18.000 1.0843 0.06340 0.05783 0.0902 0.0292 0.9900 18.250 1.0872 0.06576 0.06030 0.0903 0.0287 0.9912 18.500 1.0889 0.06821 0.06285 0.0905 0.0283 0.9926 18.750 1.0912 0.07075 0.06548 0.0903 0.0278 0.9937 19.000 1.0958 0.07339 0.06819 0.0893 0.0274 0.9941 19.250 1.1002 0.07606 0.07092 0.0882 0.0270 0.9946