XFOIL Version 6.96 Calculated polar for: NACA 16-006 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 ------ -------- --------- --------- -------- -------- -------- -9.000 -0.5161 0.08279 0.08125 -0.0118 1.0000 0.0059 -8.750 -0.5202 0.07815 0.07662 -0.0134 1.0000 0.0059 -8.500 -0.5257 0.07334 0.07183 -0.0155 1.0000 0.0059 -8.250 -0.5336 0.06836 0.06686 -0.0187 1.0000 0.0059 -8.000 -0.5470 0.06339 0.06188 -0.0227 1.0000 0.0059 -7.750 -0.5596 0.05949 0.05799 -0.0228 1.0000 0.0059 -7.500 -0.5664 0.05514 0.05359 -0.0227 1.0000 0.0059 -7.250 -0.5712 0.05091 0.04926 -0.0218 1.0000 0.0059 -7.000 -0.5744 0.04681 0.04508 -0.0203 1.0000 0.0059 -6.750 -0.5765 0.04291 0.04109 -0.0182 1.0000 0.0059 -6.500 -0.5774 0.03916 0.03725 -0.0156 1.0000 0.0059 -4.000 -0.4109 0.01489 0.01005 -0.0075 0.9866 0.0049 -3.750 -0.3843 0.01240 0.00725 -0.0065 0.9850 0.0040 -3.500 -0.3589 0.01041 0.00505 -0.0054 0.9832 0.0033 -3.250 -0.3326 0.00919 0.00365 -0.0049 0.9814 0.0029 -3.000 -0.3041 0.00853 0.00286 -0.0051 0.9800 0.0027 -2.750 -0.2746 0.00811 0.00234 -0.0055 0.9786 0.0025 -2.500 -0.2444 0.00784 0.00191 -0.0061 0.9775 0.0023 -2.250 -0.2160 0.00762 0.00163 -0.0063 0.9754 0.0022 -2.000 -0.1889 0.00746 0.00141 -0.0063 0.9723 0.0022 -1.750 -0.1601 0.00732 0.00126 -0.0066 0.9700 0.0024 -1.500 -0.1307 0.00721 0.00114 -0.0071 0.9679 0.0030 -1.250 -0.1009 0.00711 0.00108 -0.0077 0.9660 0.0044 -1.000 -0.0787 0.00641 0.00099 -0.0069 0.9613 0.1786 -0.750 -0.0704 0.00429 0.00077 -0.0036 0.9552 0.7261 -0.500 -0.0525 0.00377 0.00087 -0.0011 0.9505 0.8911 -0.250 -0.0273 0.00376 0.00094 -0.0002 0.9445 0.9245 0.000 0.0000 0.00376 0.00095 0.0000 0.9369 0.9369 0.250 0.0273 0.00376 0.00094 0.0002 0.9245 0.9445 0.500 0.0525 0.00377 0.00087 0.0011 0.8903 0.9505 0.750 0.0705 0.00428 0.00077 0.0036 0.7268 0.9552 1.000 0.0784 0.00646 0.00100 0.0069 0.1646 0.9614 1.250 0.1010 0.00711 0.00108 0.0077 0.0044 0.9661 1.500 0.1307 0.00721 0.00114 0.0071 0.0030 0.9679 1.750 0.1601 0.00732 0.00126 0.0066 0.0024 0.9700 2.000 0.1889 0.00746 0.00141 0.0063 0.0022 0.9724 2.250 0.2159 0.00762 0.00163 0.0064 0.0022 0.9755 2.500 0.2444 0.00784 0.00191 0.0061 0.0023 0.9775 2.750 0.2746 0.00812 0.00235 0.0055 0.0025 0.9787 3.000 0.3042 0.00853 0.00286 0.0051 0.0026 0.9800 3.250 0.3327 0.00920 0.00366 0.0049 0.0029 0.9815 3.500 0.3590 0.01041 0.00505 0.0054 0.0033 0.9832 3.750 0.3844 0.01241 0.00727 0.0065 0.0040 0.9851 4.000 0.4112 0.01489 0.01005 0.0074 0.0049 0.9867 8.000 0.6373 0.07715 0.07558 0.0154 0.0058 1.0000 8.250 0.6352 0.08161 0.08007 0.0132 0.0058 1.0000 8.500 0.6307 0.08655 0.08501 0.0083 0.0058 1.0000