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. max_iterations ( int, optional) – Maximum number of iterations for the camber line solver.Must fall in order for the camber line solver to terminate. camber_termination_tol ( float, optional) – The tolerance below which the maximum approximate error in the camber line estimate.The camber line intersects the front of the profile). The camber line solver will try to iteratively find the leading edge (the point where THIS POINT SHOULD LIE ON THE AIRFOIL OUTLINE. If this is given, the camber line will be forced le_loc ( list, optional) – Gives the location of the leading edge relative to the given points for an airfoilĭefined by a set of outline points.Iteration of the camber line solver should be accepted. camber_relaxation ( float, optional) – A value between 0.0 and 1.0 that defines how much of the update at each.verbose ( bool, optional) – Whether to display information on the progress of parameterizing the geometryįor an airfoil defined by a set of outline points.airfoil_input ( dict or str) – Dictionary or path to JSON object describing the airfoil.If export_polynomial_fits() is used, these values are the same as those for the Specified as constant when the database was generated.įor ‘poly_fit’ airfoils, ‘Mach’ and ‘Rey’ default to the values given in the fit file. If the database is dependent on that variable. When using the member methods get_CL, get_CD, get_Cm, get_CLa, get_CLM, get_CLRe,Īnd get_aL0, the default parameters are dependent upon the type of airfoil.įor all airfoil types except ‘functional’, ‘alpha’, ‘trailing_flap_deflection’,Īnd ‘trailing_flap_fraction’ default to 0.0.įor ‘functional’ airfoils, the defaults are specified by the user.įor ‘linear’ airfoils, ‘Mach’ and ‘Rey’ have no effect on computations.įor ‘database’ airfoils, ‘Mach’ and ‘Rey’ default to the average value in the database, The parameters “camber_relaxation”, “le_loc”, and “camber_termination_tol” then Run to determine the camber line and thickness distribution of the airfoil. Points, then when this class is initialized, a solver will be automatically If the airfoil geometry is defined using outline Airfoil ( name, airfoil_input, **kwargs ) ¶Ī class defining an airfoil. The following member functions are available: class airfoil_db. For an example of using the Airfoil class to generate and export a database, see the examples/ directory. The Airfoil class can create geometries, create a database using Xfoil, export and import databases, curve fit a database, import and export curve fits, and calculate section properties. All functionality is wrapped in the Airfoil class.
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