![]() # Single Mach Number present, Create 1D splinesĪirfoil_data_ type = '1D' cd_spline = (alpha_data, cd_data)Ĭl_spline = (alpha_data,cl_data)Ĭm_spline = (alpha_data,cm_data) # Determine Mach Range if min(mach_data) = max(mach_data): Print 'root_airfoil_name is not defined in the inputs file' print 'Exiting!'Īirfoil_ type = 'single' # Read airfoil data if airfoil_ type = 'single':Īirfoil = np.loadtxt( './airfoils/'+airfoil_name+ '.dat',skiprows= 1,delimiter= ',') # tip_airfoil_name exists, see if root_airfoil_name exists Print 'Neither airfoil_name nor tip_airfoil_name in inputs file' print 'Exiting!' # airfoil_name is not defined, see if tip & root airfoil names exist Makes the angle of attack smaller # alpha_rad - The effective angle of attack the airfoil experiences # alpha_rad + phi = theta # Rotor Blade Element Analysis # Python Script for determining Rotor Performance using Blade Element Theory # Definitions # theta - The physical angle the airfoil is rotated from the plane of rotation # phi - The change in flow angle due to the induced airflow. Added support for Mach and alpha airfoil coeffs vs just alpha. Additionally switched to using splines for the airfoil data instead of fits done in a spreadsheet. ![]() ![]() Added logic to notify the user if the case doesn't convergeīroke out the inputs into a file (inputs.txt), keeping the code cleaner. In the process the code was polished up and some improvements were made.įound that the code would not converge for some cases and the user wouldn't know. Recently, the rotor designs were re-visited to double check some of the design assumptions.
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