XFOIL Version 6.96 Calculated polar for: FX60-100 10.0% smoothed 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.000 -0.3807 0.08919 0.08418 -0.0425 1.0000 0.0261 -8.750 -0.3811 0.08618 0.08124 -0.0424 1.0000 0.0257 -8.500 -0.3838 0.08304 0.07817 -0.0425 1.0000 0.0253 -8.250 -0.3893 0.07992 0.07511 -0.0424 1.0000 0.0250 -8.000 -0.3995 0.07679 0.07209 -0.0419 1.0000 0.0246 -7.750 -0.4145 0.07391 0.06935 -0.0407 1.0000 0.0243 -7.500 -0.4287 0.07016 0.06570 -0.0409 1.0000 0.0240 -7.250 -0.4410 0.06486 0.06045 -0.0439 1.0000 0.0235 -7.000 -0.4510 0.05778 0.05330 -0.0512 1.0000 0.0230 -6.750 -0.4447 0.05040 0.04559 -0.0599 0.9979 0.0224 -6.500 -0.4131 0.04324 0.03783 -0.0703 0.9922 0.0226 -6.250 -0.3790 0.03826 0.03223 -0.0770 0.9872 0.0239 -6.000 -0.3418 0.03417 0.02744 -0.0823 0.9835 0.0248 -5.750 -0.3076 0.03092 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