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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.500 -0.2272 0.09120 0.08650 -0.0236 0.5252 0.0243 -9.250 -0.2250 0.08746 0.08274 -0.0248 0.5235 0.0243 -9.000 -0.2229 0.08361 0.07889 -0.0261 0.5217 0.0243 -8.750 -0.2215 0.07970 0.07500 -0.0274 0.5198 0.0243 -8.250 -0.2863 0.08321 0.07819 -0.0328 0.5226 0.0176 -8.000 -0.2854 0.07998 0.07499 -0.0339 0.5203 0.0174 -7.750 -0.2861 0.07683 0.07187 -0.0349 0.5183 0.0171 -7.500 -0.2869 0.07413 0.06917 -0.0354 0.5163 0.0165 -7.250 -0.2922 0.06960 0.06463 -0.0379 0.5149 0.0169 -7.000 -0.2895 0.06599 0.06098 -0.0394 0.5130 0.0164 -6.750 -0.2852 0.06213 0.05704 -0.0409 0.5114 0.0161 -6.500 -0.2805 0.05745 0.05223 -0.0425 0.5100 0.0164 -6.250 -0.2747 0.05045 0.04493 -0.0440 0.5090 0.0177 -6.000 -0.2651 0.04680 0.04111 -0.0436 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