XFOIL Version 6.94 Calculated polar for: Eiffel 430 (Lachassgne) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.022 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.3012 0.06618 0.05795 0.0128 0.9538 0.4567 -2.750 -0.2584 0.06536 0.05654 -0.0001 0.9493 0.3817 -2.500 -0.2466 0.06194 0.05301 -0.0017 0.9454 0.3550 -2.250 -0.2161 0.06066 0.05118 -0.0079 0.9406 0.3167 -2.000 -0.1900 0.06132 0.05163 -0.0092 0.9356 0.3058 -1.750 -0.1784 0.05767 0.04791 -0.0093 0.9309 0.3138 -1.500 -0.1702 0.05513 0.04550 -0.0074 0.9259 0.3354 -1.250 -0.1553 0.05409 0.04449 -0.0064 0.9201 0.3595 -1.000 -0.1300 0.05318 0.04337 -0.0081 0.9143 0.3661 -0.750 -0.0963 0.05233 0.04214 -0.0114 0.9088 0.3601 -0.500 -0.0600 0.05195 0.04139 -0.0150 0.9041 0.3601 -0.250 -0.0223 0.05204 0.04112 -0.0188 0.9004 0.3661 0.000 0.0041 0.05208 0.04084 -0.0206 0.8981 0.3762 0.250 0.0255 0.05152 0.04003 -0.0212 0.8900 0.3907 0.500 0.0685 0.04995 0.03848 -0.0258 0.8824 0.4531 1.000 0.2056 0.05078 0.04032 -0.0458 0.8600 1.0000 1.250 0.2283 0.05267 0.04176 -0.0473 0.8487 1.0000 1.500 0.2504 0.05470 0.04340 -0.0488 0.8384 1.0000 1.750 0.2712 0.05684 0.04523 -0.0502 0.8305 1.0000 2.000 0.2881 0.05900 0.04713 -0.0510 0.8257 1.0000 2.250 0.3017 0.06112 0.04906 -0.0513 0.8230 1.0000 2.500 0.3232 0.06356 0.05170 -0.0527 0.8176 1.0000 2.750 0.3933 0.07109 0.05877 -0.0605 0.7987 1.0000 3.000 0.3870 0.07039 0.05793 -0.0572 0.7921 1.0000 3.250 0.3850 0.07081 0.05822 -0.0548 0.7857 1.0000 3.500 0.3907 0.07264 0.05991 -0.0540 0.7843 1.0000 3.750 0.3995 0.07512 0.06227 -0.0538 0.7858 1.0000 4.000 0.4097 0.07798 0.06501 -0.0540 0.7881 1.0000 4.250 0.4228 0.08164 0.06857 -0.0547 0.7915 1.0000 4.750 0.3445 0.08120 0.06818 -0.0437 0.8918 1.0000 5.000 0.2521 0.07725 0.06429 -0.0246 0.9992 1.0000