2. Aerodynamic Module Documentation¶
2.1. Lifting Line Theory¶
If \(\theta_0\) is an arbitrary span-wise location:
Each equation has \(N\) unknowns (\(A_n\)), so if there are N \(\theta_o\), we have NxN system, which in Einstein notation can be written as:
where, \(i=0,...,N\), \(j=0,...,N\) and :
where \(n=1,3,5,...,N-1\). Since we are considering a symmetric wing, all of the even terms would cancel each other
2.2. The code¶
Current funcionatilities: - Lifting line theory - generate field pressures for Abaqus or other softwares - air properties calculator - Reynolds calculator Created on Mon Jul 20 17:26:19 2015
@author: Pedro Leal
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aeropy.aero_module.
LLT_calculator
(alpha_L_0_root, c_D_xfoil, N=10, b=10.0, taper=1.0, chord_root=1, alpha_root=0.0, V=1.0)[source]¶ Calculate the coefficients for a Wing. TODO : - Include elliptical wing
- When alpha_L_0_root = zero, nan!
- Include non rectangular wings
- something else?
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aeropy.aero_module.
Reynolds
(height, V, c)[source]¶ Simple function to calculate Reynolds for a given height.
@author: Pedro Leal Created in Jul 17 2015
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aeropy.aero_module.
air_properties
(height, unit='feet')[source]¶ Function to calculate air properties for a given height (m or ft).
- Sources:
Created on Thu May 15 14:59:43 2014 @author: Pedro Leal
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aeropy.aero_module.
calculate_moment_coefficient
(x, y, Cp, alpha, c=1.0, x_ref=0.25, y_ref=0.0, flap=False)[source]¶ Calculate the moment coeffcient. Inputs are x and y coordinates, and pressure coefficients (Cp). Inputs can be in a list in xfoil format (counterclockwise starting from the trailing edge, in case necessary, check create_input function from xfoil_module) or dictionaries with ‘upper’ and ‘lower’ keys.
Parameters: flap – if true, also calculates the moment contribution from the trailing edge and the panels in front of the flap (that are not directly in contact with the air)
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aeropy.aero_module.
pressure_shell
(Data, half_span, chord='MAX', air_density=0, Velocity=0, N=10, thickness=0, txt=False, llt_distribution=False, distribution='Uniform', amplifier=1)[source]¶ Converts pressure coefficient data, usually 2D, into a 3D presurre field that Abaqus understands. Can be used for shells (considers thicknesses), but also for any surface. Can do Lifting Line Theory (LLT), Elliptical, and Uniform distributions.
If chord=’MAX’, the maximum value for vector ‘x’ is used as chord. If data in non-dimensional, use a numerical value.
If txt==True, an output textfile is generated.