XFOIL Version 6.96 Calculated polar for: FX 84-W-097 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.000 -0.3428 0.10662 0.10011 -0.0236 1.0000 0.0724 -9.750 -0.3386 0.10250 0.09602 -0.0245 1.0000 0.0696 -9.500 -0.4360 0.10508 0.09818 -0.0243 1.0000 0.0610 -9.250 -0.4267 0.10127 0.09438 -0.0244 1.0000 0.0592 -9.000 -0.4233 0.09738 0.09054 -0.0261 1.0000 0.0582 -8.750 -0.4221 0.09338 0.08662 -0.0284 1.0000 0.0579 -8.500 -0.4217 0.08939 0.08271 -0.0307 1.0000 0.0576 -8.250 -0.4232 0.08531 0.07872 -0.0333 1.0000 0.0576 -8.000 -0.4265 0.08119 0.07469 -0.0362 1.0000 0.0573 -7.750 -0.4286 0.07678 0.07035 -0.0395 1.0000 0.0568 -7.500 -0.4304 0.07225 0.06586 -0.0425 1.0000 0.0564 -7.250 -0.4326 0.06786 0.06147 -0.0447 1.0000 0.0559 -7.000 -0.4360 0.06375 0.05732 -0.0457 1.0000 0.0554 -6.750 -0.4411 0.06004 0.05354 -0.0455 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