XFOIL Version 6.94 Calculated polar for: gradus2 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.080 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -2.500 -0.2424 0.02476 0.01493 0.0033 0.9999 0.1589 -2.000 -0.1989 0.02437 0.01618 0.0065 0.9999 0.4441 -1.500 -0.1459 0.02596 0.01761 0.0081 0.9877 0.5385 -1.000 0.0203 0.02431 0.01594 -0.0122 0.9313 0.6309 -0.500 0.2555 0.01932 0.00868 -0.0424 0.3934 0.7026 0.000 0.4619 0.02061 0.00997 -0.0759 0.3421 0.9778 0.500 0.5531 0.02204 0.01093 -0.0838 0.3279 1.0001 1.000 0.6172 0.02312 0.01171 -0.0856 0.3194 1.0001 1.500 0.6803 0.02450 0.01284 -0.0872 0.3131 1.0001 2.000 0.7376 0.02562 0.01399 -0.0875 0.3058 1.0001 2.500 0.7939 0.02712 0.01535 -0.0878 0.2972 1.0001 3.000 0.8469 0.02867 0.01701 -0.0873 0.2904 1.0001 3.500 0.8979 0.03021 0.01872 -0.0865 0.2839 1.0001 4.000 0.9484 0.03211 0.02069 -0.0857 0.2788 1.0001 4.500 0.9967 0.03492 0.02361 -0.0848 0.2751 1.0001 5.000 1.0390 0.03710 0.02627 -0.0824 0.2725 1.0001