XFOIL Version 6.94 Calculated polar for: BOIS RENAN G. 3 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.012 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -2.750 -0.4709 0.06598 0.05251 0.0593 0.9998 0.7609 -2.500 -0.1029 0.06794 0.05362 -0.0157 0.9998 1.0002 -2.250 -0.1336 0.06535 0.05086 -0.0126 0.9998 1.0002 -2.000 -0.1366 0.06423 0.04891 -0.0135 0.9998 1.0002 -1.750 -0.1198 0.06467 0.04832 -0.0154 0.9998 1.0002 -1.500 -0.1013 0.06558 0.04843 -0.0163 0.9998 1.0002 -1.250 -0.0843 0.06666 0.04885 -0.0165 0.9998 1.0002 -1.000 -0.0679 0.06778 0.04944 -0.0164 0.9998 1.0002 -0.750 -0.0527 0.06900 0.05021 -0.0161 0.9998 1.0002 -0.500 -0.0374 0.07022 0.05102 -0.0158 0.9998 1.0002 -0.250 -0.0229 0.07153 0.05200 -0.0155 0.9998 1.0002 0.500 0.0201 0.07585 0.05542 -0.0145 0.9998 1.0002 0.750 0.0347 0.07733 0.05672 -0.0142 0.9998 1.0002 1.000 0.0485 0.07892 0.05809 -0.0140 0.9998 1.0002 1.250 0.0627 0.08054 0.05953 -0.0138 0.9998 1.0002 1.500 0.0761 0.08219 0.06101 -0.0138 0.9998 1.0002 1.750 0.0903 0.08391 0.06257 -0.0136 0.9998 1.0002 2.000 0.1045 0.08566 0.06419 -0.0135 0.9998 1.0002 2.250 0.1182 0.08746 0.06588 -0.0136 0.9998 1.0002 2.500 0.1316 0.08938 0.06770 -0.0136 0.9998 1.0002 2.750 0.1453 0.09129 0.06949 -0.0137 0.9998 1.0002 3.000 0.1588 0.09327 0.07140 -0.0138 0.9998 1.0002 3.250 0.1720 0.09530 0.07335 -0.0139 0.9998 1.0002 3.500 0.1856 0.09737 0.07534 -0.0140 0.9998 1.0002 3.750 0.1988 0.09939 0.07732 -0.0143 0.9998 1.0002 4.000 0.2115 0.10165 0.07955 -0.0145 0.9998 1.0002 4.250 0.2248 0.10377 0.08162 -0.0148 0.9998 1.0002 4.500 0.2379 0.10608 0.08396 -0.0150 0.9998 1.0002 4.750 0.2506 0.10833 0.08617 -0.0154 0.9998 1.0002 5.000 0.2633 0.11070 0.08853 -0.0157 0.9998 1.0002