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 = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.500 -0.2078 0.09238 0.08802 -0.0213 0.5877 0.0362 -9.250 -0.2034 0.08914 0.08474 -0.0222 0.5852 0.0370 -9.000 -0.2003 0.08580 0.08137 -0.0232 0.5830 0.0378 -8.750 -0.1978 0.08235 0.07795 -0.0243 0.5801 0.0388 -8.500 -0.1963 0.07885 0.07446 -0.0256 0.5779 0.0398 -8.250 -0.1961 0.07531 0.07092 -0.0269 0.5756 0.0409 -8.000 -0.1983 0.07187 0.06750 -0.0288 0.5739 0.0423 -7.750 -0.2056 0.06851 0.06416 -0.0318 0.5726 0.0434 -7.500 -0.2112 0.06517 0.06083 -0.0344 0.5712 0.0437 -7.250 -0.2279 0.06206 0.05772 -0.0381 0.5702 0.0441 -7.000 -0.2321 0.05833 0.05393 -0.0401 0.5689 0.0443 -6.750 -0.2324 0.05443 0.04994 -0.0415 0.5673 0.0444 -6.250 -0.2556 0.05993 0.05494 -0.0463 0.5669 0.0458 -6.000 -0.2431 0.05765 0.05271 -0.0454 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