XFOIL Version 6.94 Calculated polar for: SD5060 (9.5%) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.2409 0.00623 0.00187 -0.0491 0.7343 0.8276 0.500 0.3041 0.00601 0.00179 -0.0495 0.7082 0.9757 1.500 0.4217 0.00629 0.00172 -0.0502 0.6495 1.0000 2.000 0.4763 0.00650 0.00178 -0.0496 0.6149 1.0000 2.500 0.5310 0.00675 0.00187 -0.0491 0.5769 1.0000 3.000 0.5853 0.00707 0.00203 -0.0486 0.5329 1.0000 3.500 0.6390 0.00750 0.00224 -0.0481 0.4801 1.0000 4.000 0.6923 0.00800 0.00255 -0.0476 0.4218 1.0000 4.500 0.7444 0.00869 0.00294 -0.0470 0.3519 1.0000 5.000 0.7959 0.00946 0.00344 -0.0464 0.2877 1.0000 5.500 0.8468 0.01031 0.00404 -0.0457 0.2321 1.0000 6.000 0.8979 0.01110 0.00468 -0.0451 0.1907 1.0000 6.500 0.9486 0.01191 0.00540 -0.0443 0.1610 1.0000 7.000 0.9986 0.01275 0.00616 -0.0435 0.1367 1.0000 7.500 1.0478 0.01363 0.00704 -0.0426 0.1182 1.0000 8.000 1.0968 0.01449 0.00792 -0.0417 0.1021 1.0000 8.500 1.1451 0.01534 0.00881 -0.0407 0.0859 1.0000 9.000 1.1921 0.01628 0.00979 -0.0395 0.0697 1.0000 9.500 1.2367 0.01738 0.01087 -0.0382 0.0536 1.0000 10.000 1.2783 0.01869 0.01220 -0.0365 0.0410 1.0000 10.500 1.3166 0.02018 0.01377 -0.0344 0.0307 1.0000 11.000 1.3446 0.02242 0.01604 -0.0311 0.0194 1.0000 11.500 1.3595 0.02501 0.01879 -0.0262 0.0137 1.0000 12.000 1.3735 0.02730 0.02128 -0.0217 0.0115 1.0000 12.500 1.3708 0.03116 0.02534 -0.0173 0.0101 1.0000 13.000 1.3676 0.03574 0.03021 -0.0146 0.0094 1.0000 13.500 1.3648 0.04100 0.03575 -0.0135 0.0090 1.0000 14.000 1.3562 0.04765 0.04270 -0.0140 0.0085 1.0000 14.500 1.3419 0.05590 0.05124 -0.0163 0.0081 1.0000 15.000 1.3227 0.06584 0.06147 -0.0203 0.0080 1.0000 15.500 1.2992 0.07754 0.07347 -0.0260 0.0079 1.0000 16.000 1.2720 0.09104 0.08725 -0.0332 0.0078 1.0000 16.500 1.2441 0.10553 0.10202 -0.0412 0.0078 1.0000 17.000 1.2157 0.12091 0.11766 -0.0499 0.0077 1.0000 17.500 1.1884 0.13672 0.13373 -0.0591 0.0078 1.0000 18.000 1.1611 0.15341 0.15066 -0.0691 0.0078 1.0000 18.500 1.1254 0.17361 0.17116 -0.0814 0.0080 1.0000