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 = 0.030 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.0878 0.04001 0.03036 -0.0294 0.9995 0.3734 -2.750 -0.0636 0.03958 0.02987 -0.0297 0.9995 0.3896 -2.500 -0.0010 0.03813 0.02830 -0.0363 0.9835 0.4189 -2.250 0.1374 0.03357 0.02440 -0.0530 0.9347 0.5189 -2.000 0.2146 0.02989 0.02175 -0.0552 0.8777 1.0005 -1.750 0.2381 0.03090 0.02215 -0.0505 0.8253 1.0005 -1.500 0.2500 0.03213 0.02302 -0.0439 0.7668 1.0005 -1.250 0.2591 0.03347 0.02399 -0.0364 0.6984 1.0005 -1.000 0.2732 0.03473 0.02480 -0.0307 0.6292 1.0005 -0.750 0.2951 0.03545 0.02510 -0.0275 0.5793 1.0005 -0.500 0.3238 0.03623 0.02558 -0.0271 0.5411 1.0005 -0.250 0.3517 0.03684 0.02587 -0.0262 0.5165 1.0005 0.000 0.3805 0.03755 0.02631 -0.0258 0.4956 1.0005 0.250 0.4097 0.03842 0.02693 -0.0258 0.4778 1.0005 0.500 0.4369 0.03897 0.02716 -0.0246 0.4655 1.0005 0.750 0.4694 0.04092 0.02908 -0.0270 0.4526 1.0005 1.000 0.4970 0.04183 0.02972 -0.0263 0.4441 1.0005 1.250 0.5298 0.04454 0.03253 -0.0298 0.4331 1.0005 1.500 0.5570 0.04551 0.03327 -0.0291 0.4254 1.0005 1.750 0.5874 0.04879 0.03665 -0.0329 0.4186 1.0005 2.000 0.6161 0.05305 0.04106 -0.0378 0.4147 1.0005 2.250 0.6407 0.05768 0.04581 -0.0426 0.4124 1.0005 2.500 0.6601 0.06289 0.05112 -0.0476 0.4109 1.0005 2.750 0.6725 0.06892 0.05724 -0.0530 0.4108 1.0005 3.000 0.6755 0.07585 0.06426 -0.0588 0.4140 1.0005 3.250 0.6802 0.08171 0.07013 -0.0626 0.4191 1.0005 3.500 0.6929 0.08639 0.07479 -0.0647 0.4242 1.0005 3.750 0.6740 0.09527 0.08372 -0.0710 0.4447 1.0005