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 = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.000 -0.3062 0.09783 0.09420 -0.0272 0.4509 0.0048 -9.750 -0.2962 0.09593 0.09229 -0.0283 0.4493 0.0056 -8.250 -0.5619 0.02156 0.01648 -0.0402 0.4530 0.0059 -8.000 -0.5428 0.02031 0.01501 -0.0389 0.4511 0.0062 -7.750 -0.5256 0.01870 0.01311 -0.0372 0.4495 0.0063 -7.500 -0.5066 0.01731 0.01147 -0.0356 0.4484 0.0063 -7.250 -0.4819 0.01697 0.01104 -0.0350 0.4472 0.0064 -7.000 -0.4597 0.01610 0.01000 -0.0339 0.4459 0.0065 -6.750 -0.4381 0.01511 0.00880 -0.0327 0.4445 0.0067 -6.500 -0.4153 0.01432 0.00787 -0.0317 0.4432 0.0070 -6.250 -0.3904 0.01393 0.00740 -0.0310 0.4417 0.0073 -6.000 -0.3659 0.01344 0.00681 -0.0303 0.4404 0.0074 -5.750 -0.3410 0.01303 0.00632 -0.0296 0.4392 0.0076 -5.500 -0.3151 0.01279 0.00603 -0.0291 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