![]() NACA – Boolean variable that defines if the code imports anĪirfoil from a file or generates a NACA airfoil.plots – the code is able to save in a.Reynolds number different from zero must also be informed. For logical reasons, if Mach is informed a If not informed, the code will not use theĬorrection. Mach – Mach number in case the simulation has to take inĪccount compressibility effects through the Prandtl-GlauertĬorrelation.In case not informed, the code will assume Reynolds – Reynolds number in case the simulation is for a.Coordinates: returns the coordinates of a NACA airfoil.Alfa_L_0: generates a file with the value of the angle of attack that lift is equal to zero.Polar: generates file with CL, CD, CM, CDp, Top_Xtr, Bot_Xtr.Dump: generates file with Velocity along surface, Delta star,theta and Cf vs s,x,y for several alfas.Cp: generates files with Pressure coefficients for desired alfas.There are four posssible choices (by default, Cp is chosen): output – defines the kind of output desired from xfoil.alfas – list/array/float/int of angles of attack.If NACA is True, airfoil is the naca series of the airfoil airfoil – if NACA is false, airfoil is the name of the plainįilewhere the airfoil geometry is stored (variable airfoil).call ( airfoil, alfas='none', output='Cp', Reynolds=0, Mach=0, plots=False, NACA=True, GDES=False, iteration=10, flap=None, PANE=False, NORM=True ) ¶
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