XFOIL Version 6.94 Calculated polar for: agora10 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.005 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.0791 0.05656 0.03831 -0.0026 0.9992 1.0008 -2.750 -0.0626 0.05589 0.03683 -0.0063 0.9992 1.0008 -2.500 -0.0416 0.05593 0.03604 -0.0091 0.9992 1.0008 -2.250 -0.0219 0.05633 0.03575 -0.0109 0.9992 1.0008 -2.000 -0.0043 0.05698 0.03579 -0.0118 0.9992 1.0008 -1.750 0.0118 0.05780 0.03610 -0.0124 0.9992 1.0008 -1.500 0.0273 0.05875 0.03660 -0.0127 0.9992 1.0008 -1.250 0.0426 0.05982 0.03727 -0.0131 0.9992 1.0008 -1.000 0.0575 0.06101 0.03811 -0.0134 0.9992 1.0008 -0.750 0.0723 0.06232 0.03914 -0.0139 0.9992 1.0008 -0.500 0.0868 0.06378 0.04035 -0.0145 0.9992 1.0008 -0.250 0.1009 0.06540 0.04177 -0.0153 0.9992 1.0008 0.000 0.1143 0.06720 0.04341 -0.0163 0.9992 1.0008 0.250 0.1268 0.06920 0.04527 -0.0175 0.9992 1.0008 0.500 0.1382 0.07142 0.04736 -0.0189 0.9992 1.0008 0.750 0.1487 0.07383 0.04964 -0.0205 0.9992 1.0008 1.000 0.1587 0.07641 0.05207 -0.0222 0.9992 1.0008 1.250 0.1684 0.07909 0.05459 -0.0240 0.9992 1.0008 1.500 0.1781 0.08183 0.05717 -0.0258 0.9992 1.0008 1.750 0.1879 0.08460 0.05977 -0.0276 0.9992 1.0008 2.000 0.1980 0.08738 0.06240 -0.0294 0.9992 1.0008 2.250 0.2083 0.09018 0.06503 -0.0311 0.9992 1.0008 2.500 0.2188 0.09299 0.06769 -0.0328 0.9992 1.0008 2.750 0.2296 0.09584 0.07038 -0.0345 0.9992 1.0008 3.000 0.2407 0.09871 0.07309 -0.0362 0.9992 1.0008 3.250 0.2519 0.10158 0.07582 -0.0379 0.9992 1.0008 3.500 0.2632 0.10446 0.07855 -0.0395 0.9992 1.0008 3.750 0.2746 0.10735 0.08130 -0.0412 0.9992 1.0008 4.000 0.2862 0.11026 0.08406 -0.0428 0.9992 1.0008 4.250 0.2978 0.11317 0.08683 -0.0444 0.9992 1.0008 4.500 0.3096 0.11609 0.08962 -0.0460 0.9992 1.0008 4.750 0.3214 0.11902 0.09242 -0.0476 0.9992 1.0008 5.000 0.3334 0.12195 0.09523 -0.0492 0.9992 1.0008