XFOIL Version 6.94 Calculated polar for: SG6040 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 0.3918 0.00896 0.00337 -0.0909 0.6875 0.6710 0.500 0.4468 0.00903 0.00339 -0.0907 0.6713 0.6790 1.000 0.5017 0.00910 0.00338 -0.0905 0.6549 0.6862 1.500 0.5560 0.00918 0.00344 -0.0902 0.6389 0.6930 2.000 0.6102 0.00932 0.00352 -0.0899 0.6225 0.7006 2.500 0.6641 0.00944 0.00359 -0.0896 0.6062 0.7075 3.000 0.7169 0.00958 0.00375 -0.0890 0.5895 0.7152 3.500 0.7697 0.00975 0.00391 -0.0884 0.5724 0.7231 4.000 0.8202 0.00991 0.00410 -0.0874 0.5529 0.7316 4.500 0.8697 0.01015 0.00430 -0.0862 0.5315 0.7410 5.000 0.9177 0.01035 0.00455 -0.0848 0.5094 0.7508 5.500 0.9650 0.01063 0.00484 -0.0832 0.4868 0.7627 6.000 1.0103 0.01090 0.00518 -0.0812 0.4643 0.7750 6.500 1.0514 0.01128 0.00556 -0.0785 0.4373 0.7896 7.000 1.0903 0.01167 0.00599 -0.0754 0.4087 0.8079 7.500 1.1206 0.01215 0.00650 -0.0707 0.3792 0.8309 8.000 1.1479 0.01274 0.00713 -0.0655 0.3447 0.8637 8.500 1.1714 0.01339 0.00787 -0.0599 0.3015 0.9910 9.500 1.2071 0.01666 0.01055 -0.0495 0.1921 1.0000 10.000 1.2204 0.01871 0.01237 -0.0444 0.1501 1.0000 10.500 1.2352 0.02087 0.01438 -0.0399 0.1192 1.0000 11.000 1.2506 0.02317 0.01662 -0.0360 0.0966 1.0000 11.500 1.2641 0.02577 0.01918 -0.0324 0.0801 1.0000 12.000 1.2771 0.02861 0.02205 -0.0293 0.0688 1.0000 12.500 1.2876 0.03185 0.02533 -0.0265 0.0606 1.0000 13.000 1.2958 0.03552 0.02905 -0.0241 0.0544 1.0000 13.500 1.3061 0.03927 0.03294 -0.0223 0.0500 1.0000 14.000 1.3129 0.04360 0.03736 -0.0209 0.0463 1.0000 14.500 1.3136 0.04881 0.04270 -0.0199 0.0433 1.0000 15.000 1.3231 0.05343 0.04749 -0.0195 0.0408 1.0000 15.500 1.3267 0.05889 0.05305 -0.0196 0.0383 1.0000 16.000 1.3242 0.06526 0.05954 -0.0200 0.0362 1.0000 16.500 1.3313 0.07081 0.06529 -0.0208 0.0346 1.0000 17.000 1.3357 0.07687 0.07151 -0.0220 0.0330 1.0000 17.500 1.3376 0.08344 0.07820 -0.0236 0.0316 1.0000 18.000 1.3377 0.08998 0.08484 -0.0249 0.0302 1.0000 18.500 1.3415 0.09672 0.09181 -0.0272 0.0294 1.0000 19.000 1.3429 0.10389 0.09921 -0.0299 0.0284 1.0000 19.500 1.3432 0.11133 0.10684 -0.0330 0.0274 1.0000 20.000 1.3431 0.11890 0.11456 -0.0365 0.0265 1.0000 20.500 1.3435 0.12630 0.12209 -0.0401 0.0258 1.0000 21.000 1.3407 0.13382 0.12977 -0.0434 0.0248 1.0000 21.500 1.3295 0.14380 0.14005 -0.0493 0.0245 1.0000 22.000 1.3142 0.15482 0.15137 -0.0562 0.0241 1.0000 22.500 1.2932 0.16729 0.16415 -0.0645 0.0236 1.0000 23.000 1.2609 0.18274 0.17992 -0.0750 0.0233 1.0000