XFOIL Version 6.94 Calculated polar for: fauvel bl2 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.045 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 0.0661 0.03215 0.02256 -0.0452 0.8418 0.3185 -2.750 0.0872 0.03179 0.02225 -0.0421 0.8178 0.3320 -2.500 0.1098 0.03157 0.02192 -0.0392 0.7935 0.3476 -2.250 0.1303 0.03133 0.02167 -0.0356 0.7661 0.3695 -2.000 0.1479 0.03091 0.02139 -0.0309 0.7359 0.3981 -1.750 0.1664 0.02986 0.02086 -0.0267 0.6978 0.4608 -1.500 0.1844 0.02683 0.01917 -0.0200 0.6577 1.0005 -1.250 0.2066 0.02661 0.01837 -0.0163 0.6051 1.0005 -1.000 0.2324 0.02608 0.01741 -0.0139 0.5388 1.0005 -0.750 0.2590 0.02577 0.01650 -0.0120 0.4854 1.0005 -0.500 0.2870 0.02590 0.01600 -0.0110 0.4466 1.0005 -0.250 0.3166 0.02637 0.01596 -0.0107 0.4191 1.0005 0.000 0.3464 0.02696 0.01610 -0.0106 0.4011 1.0005 0.250 0.3770 0.02766 0.01653 -0.0108 0.3860 1.0005 0.500 0.4072 0.02844 0.01705 -0.0110 0.3741 1.0005 0.750 0.4368 0.02921 0.01753 -0.0110 0.3638 1.0005 1.000 0.4670 0.03016 0.01833 -0.0114 0.3556 1.0005 1.250 0.4977 0.03119 0.01926 -0.0118 0.3492 1.0005 1.500 0.5275 0.03224 0.02013 -0.0120 0.3441 1.0005 1.750 0.5576 0.03349 0.02123 -0.0123 0.3396 1.0005 2.000 0.5891 0.03490 0.02275 -0.0134 0.3348 1.0005 2.250 0.6196 0.03632 0.02419 -0.0143 0.3299 1.0005 2.500 0.6494 0.03776 0.02557 -0.0149 0.3257 1.0005 2.750 0.6790 0.03942 0.02719 -0.0155 0.3230 1.0005 3.000 0.7085 0.04143 0.02918 -0.0165 0.3211 1.0005 3.250 0.7389 0.04389 0.03190 -0.0185 0.3202 1.0005 3.500 0.7681 0.04682 0.03513 -0.0210 0.3193 1.0005 3.750 0.7954 0.05040 0.03904 -0.0240 0.3183 1.0005 4.000 0.8196 0.05480 0.04376 -0.0277 0.3179 1.0005 4.250 0.8397 0.05998 0.04922 -0.0315 0.3193 1.0005 4.500 0.8597 0.06447 0.05382 -0.0339 0.3212 1.0005