XFOIL Version 6.96 Calculated polar for: FX 77-W-121 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.750 -0.2840 0.08566 0.08150 -0.0314 0.4726 0.0086 -8.500 -0.2829 0.08228 0.07814 -0.0329 0.4715 0.0085 -8.250 -0.2837 0.07874 0.07462 -0.0345 0.4701 0.0083 -8.000 -0.2906 0.07456 0.07048 -0.0367 0.4692 0.0085 -7.750 -0.3001 0.07089 0.06685 -0.0381 0.4684 0.0083 -7.500 -0.3042 0.06746 0.06340 -0.0394 0.4673 0.0079 -7.250 -0.3109 0.06172 0.05763 -0.0422 0.4667 0.0084 -7.000 -0.3106 0.05685 0.05269 -0.0438 0.4657 0.0082 -6.500 -0.3080 0.04512 0.04063 -0.0449 0.4638 0.0084 -6.250 -0.3534 0.02422 0.01832 -0.0374 0.4649 0.0092 -6.000 -0.3394 0.02122 0.01478 -0.0351 0.4636 0.0094 -5.750 -0.3222 0.01893 0.01208 -0.0332 0.4623 0.0097 -5.500 -0.2974 0.01871 0.01182 -0.0327 0.4607 0.0102 -5.250 -0.2737 0.01794 0.01089 -0.0319 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