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 = 0.008 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.0945 0.07471 0.05640 -0.0212 0.9998 1.0002 -2.750 -0.1236 0.07220 0.05387 -0.0181 0.9998 1.0002 -2.500 -0.1373 0.07054 0.05167 -0.0168 0.9998 1.0002 -2.250 -0.1335 0.07015 0.05041 -0.0170 0.9998 1.0002 -2.000 -0.1211 0.07046 0.04982 -0.0174 0.9998 1.0002 -1.750 -0.1068 0.07111 0.04970 -0.0173 0.9998 1.0002 -1.500 -0.0921 0.07190 0.04983 -0.0170 0.9998 1.0002 -1.250 -0.0777 0.07282 0.05016 -0.0166 0.9998 1.0002 -1.000 -0.0631 0.07379 0.05062 -0.0161 0.9998 1.0002 -0.750 -0.0492 0.07487 0.05126 -0.0156 0.9998 1.0002 -0.500 -0.0348 0.07597 0.05192 -0.0150 0.9998 1.0002 -0.250 -0.0211 0.07715 0.05275 -0.0145 0.9998 1.0002 0.000 -0.0072 0.07841 0.05363 -0.0140 0.9998 1.0002 0.250 0.0068 0.07971 0.05462 -0.0135 0.9998 1.0002 0.500 0.0204 0.08108 0.05570 -0.0131 0.9998 1.0002 0.750 0.0345 0.08246 0.05686 -0.0127 0.9998 1.0002 1.000 0.0478 0.08393 0.05808 -0.0124 0.9998 1.0002 1.250 0.0616 0.08544 0.05938 -0.0120 0.9998 1.0002 1.500 0.0746 0.08698 0.06072 -0.0118 0.9998 1.0002 1.750 0.0885 0.08857 0.06213 -0.0116 0.9998 1.0002 2.000 0.1022 0.09025 0.06365 -0.0114 0.9998 1.0002 2.250 0.1155 0.09192 0.06518 -0.0113 0.9998 1.0002 2.500 0.1286 0.09374 0.06688 -0.0112 0.9998 1.0002 2.750 0.1420 0.09555 0.06855 -0.0111 0.9998 1.0002 3.000 0.1551 0.09743 0.07035 -0.0111 0.9998 1.0002 3.250 0.1681 0.09936 0.07219 -0.0111 0.9998 1.0002 3.500 0.1815 0.10130 0.07403 -0.0111 0.9998 1.0002 3.750 0.1942 0.10328 0.07595 -0.0113 0.9998 1.0002 4.000 0.2067 0.10541 0.07805 -0.0115 0.9998 1.0002 4.250 0.2197 0.10745 0.08003 -0.0116 0.9998 1.0002 4.500 0.2325 0.10967 0.08226 -0.0118 0.9998 1.0002 4.750 0.2449 0.11182 0.08437 -0.0121 0.9998 1.0002 5.000 0.2573 0.11409 0.08663 -0.0123 0.9998 1.0002