![]() update_type ( bool, optional) – Whether to update the airfoil to use the newly computed database for calculations.If a list, the first list element is for the top and the second list element isįor the bottom. N_crit ( float or list, optional) – Critical amplification exponent for the boundary layer in Xfoil.If a list, the first list element is the top trip location and the second list element If a float, the value is the same for the topĪnd the bottom. Specified for the top and bottom of the airfoil. x_trip ( float or list, optional) – x location, non-dimensionalized by the chord length, of the boundary layer trip position.max_iter ( int, optional) – Maximum iterations for Xfoil.N ( int, optional) – Number of panel nodes for Xfoil to use.Of airfoil properties on Reynolds number, we do not expect this to be a great hinderance. This is due to internal limitations in Xfoil. Please note that all angular degreees of freedom are in radians, rather than degrees.Ĭurrently, the number of steps in Reynolds number multiplied by the number of steps in Mach number To specify a range for the degree of freedom,Ī dictionary with the following keys should be given: Allowable degrees ofįreedom are “alpha”, “Rey”, “Mach”, “trailing_flap_deflection”, and “trailing_flap_fraction”.Įach key should be one of these degrees of freedom. Parameters:Ī dict specifying which degrees of freedom the database should perturb. Makes calls to Xfoil to calculate CL, CD, and Cm as a function of each given degree of freedom. write_limits ( bool, optional) – Whether to limit the polynomial fits based on the original range of data.filename ( str) – JSON object to write polynomial fit data to.Save the polynomial fit to a JSON object. Parameters:įilename ( str) – JSON file to export the model data to. Parameters:įilename ( str) – File to export the database to.Įxports the linear coefficients used to predict the behavior of the airfoil. May only be 4-digit series.Įxports the database generated by generate_database(). Naca_des ( str) – NACA designation of the airfoil to compare against as a string. Checks against the open trailing edge formulation of the NACA equations. ![]() If unusual geometries are being imported. This is recommended as a check for the user Defaults to 100.Ĭhecks the error in the camber and thickness against that predicted by the NACA equations.
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