XFOIL Version 6.94 Calculated polar for: St. CYR 234 (Bartel 17-IC) 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 0.6252 0.01349 0.00627 -0.0603 0.3895 0.2982 0.500 0.6497 0.01422 0.00684 -0.0553 0.3509 0.3011 1.000 0.6622 0.01545 0.00761 -0.0487 0.2767 0.3047 1.500 0.6941 0.01617 0.00810 -0.0452 0.2560 0.3379 2.000 0.7302 0.01670 0.00870 -0.0425 0.2411 0.3721 2.500 0.7699 0.01715 0.00927 -0.0403 0.2338 0.4026 3.000 0.8076 0.01743 0.00996 -0.0379 0.2284 0.5325 3.500 0.8468 0.01806 0.01061 -0.0359 0.2193 0.5723 4.000 0.8856 0.01878 0.01135 -0.0339 0.2094 0.5845 4.500 0.9245 0.01953 0.01215 -0.0321 0.2045 0.5915 5.000 0.9618 0.02037 0.01309 -0.0301 0.1997 0.5962 6.500 1.0265 0.02395 0.01680 -0.0191 0.1914 0.6151 7.000 1.0611 0.02464 0.01741 -0.0175 0.1896 0.6263 7.500 1.0968 0.02537 0.01813 -0.0162 0.1857 0.6341 8.000 1.1272 0.02637 0.01918 -0.0144 0.1709 0.6388 8.500 1.0958 0.03071 0.02327 -0.0072 0.1464 0.6388 9.000 1.0903 0.03396 0.02631 -0.0028 0.1286 0.6392 9.500 1.1056 0.03630 0.02838 -0.0005 0.1117 0.6397 10.000 1.1277 0.03834 0.03041 0.0012 0.0980 0.6404 10.500 1.1507 0.04038 0.03252 0.0025 0.0934 0.6410 11.000 1.0895 0.04928 0.04172 0.0074 0.0929 0.6406 11.500 1.1161 0.05118 0.04368 0.0079 0.0897 0.6413 12.000 1.1412 0.05321 0.04569 0.0084 0.0847 0.6421 12.500 1.1644 0.05544 0.04785 0.0087 0.0788 0.6429 13.000 1.1910 0.05740 0.04997 0.0088 0.0779 0.6437 13.500 1.2120 0.05993 0.05247 0.0088 0.0725 0.6477 14.500 1.2558 0.06490 0.05760 0.0082 0.0687 0.6902 15.500 1.2488 0.07633 0.06989 0.0062 0.0658 0.7014 16.000 1.2790 0.08224 0.07641 -0.0008 0.0623 0.9775 16.500 1.2007 0.09913 0.09375 -0.0063 0.0619 0.9801 17.000 1.2267 0.10508 0.09969 -0.0128 0.0574 0.9903 17.500 1.2593 0.11200 0.10657 -0.0217 0.0515 0.9961