XFOIL Version 6.94 Calculated polar for: fauvel bl3 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 0.1276 0.03195 0.02227 -0.0675 0.8963 0.3277 -2.750 0.1533 0.03180 0.02201 -0.0646 0.8713 0.3444 -2.500 0.1732 0.03154 0.02187 -0.0607 0.8456 0.3638 -2.250 0.1910 0.03123 0.02169 -0.0560 0.8169 0.3886 -2.000 0.2062 0.03068 0.02145 -0.0505 0.7863 0.4326 -1.750 0.2154 0.02744 0.02038 -0.0415 0.7544 1.0005 -1.500 0.2331 0.02729 0.01939 -0.0356 0.7134 1.0005 -1.250 0.2527 0.02666 0.01840 -0.0310 0.6627 1.0005 -1.000 0.2795 0.02566 0.01721 -0.0288 0.5868 1.0005 -0.750 0.3054 0.02498 0.01603 -0.0265 0.4861 1.0005 -0.500 0.3277 0.02501 0.01489 -0.0236 0.4252 1.0005 -0.250 0.3547 0.02590 0.01490 -0.0232 0.3995 1.0005 0.000 0.3828 0.02689 0.01535 -0.0230 0.3838 1.0005 0.250 0.4111 0.02789 0.01591 -0.0227 0.3734 1.0005 0.500 0.4405 0.02879 0.01661 -0.0226 0.3647 1.0005 0.750 0.4693 0.02981 0.01738 -0.0223 0.3572 1.0005 1.000 0.4994 0.03075 0.01821 -0.0224 0.3495 1.0005 1.250 0.5293 0.03176 0.01909 -0.0226 0.3430 1.0005 1.500 0.5595 0.03278 0.02003 -0.0228 0.3373 1.0005 1.750 0.5892 0.03397 0.02105 -0.0229 0.3335 1.0005 2.000 0.6199 0.03518 0.02224 -0.0234 0.3306 1.0005 2.250 0.6508 0.03643 0.02358 -0.0242 0.3279 1.0005 2.500 0.6814 0.03779 0.02501 -0.0249 0.3248 1.0005 2.750 0.7113 0.03927 0.02650 -0.0256 0.3215 1.0005 3.000 0.7406 0.04088 0.02806 -0.0261 0.3183 1.0005 3.250 0.7698 0.04276 0.02991 -0.0268 0.3159 1.0005 3.500 0.7995 0.04466 0.03203 -0.0280 0.3151 1.0005 3.750 0.8285 0.04681 0.03439 -0.0294 0.3148 1.0005 4.000 0.8564 0.04923 0.03705 -0.0308 0.3150 1.0005 4.250 0.8829 0.05197 0.04004 -0.0325 0.3150 1.0005 4.500 0.9071 0.05511 0.04346 -0.0344 0.3150 1.0005 4.750 0.9286 0.05872 0.04735 -0.0364 0.3152 1.0005