XFOIL Version 6.96 Calculated polar for: WORTMANN FX 77-W-258 AIRFOIL 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 ------ -------- --------- --------- -------- -------- -------- -17.250 -0.5747 0.13649 0.12962 -0.0145 0.5725 0.0384 -17.000 -0.6573 0.11427 0.10702 -0.0281 0.5800 0.0373 -16.750 -0.6920 0.10372 0.09616 -0.0344 0.5798 0.0371 -16.500 -0.7129 0.09625 0.08839 -0.0387 0.5775 0.0372 -16.250 -0.7277 0.09017 0.08202 -0.0418 0.5746 0.0375 -16.000 -0.7392 0.08487 0.07645 -0.0444 0.5712 0.0379 -15.750 -0.7482 0.08012 0.07143 -0.0464 0.5675 0.0383 -15.500 -0.7452 0.07728 0.06853 -0.0475 0.5628 0.0388 -15.250 -0.7420 0.07455 0.06571 -0.0484 0.5586 0.0394 -15.000 -0.7397 0.07176 0.06278 -0.0493 0.5550 0.0400 -14.750 -0.7374 0.06900 0.05985 -0.0500 0.5518 0.0407 -14.500 -0.7349 0.06629 0.05697 -0.0505 0.5483 0.0414 -14.250 -0.7320 0.06368 0.05413 -0.0509 0.5450 0.0422 -14.000 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