RCAIDE.Library.Methods.Aerodynamics.Vortex_Lattice_Method.generate_vortex_distribution
generate_vortex_distribution#
- generate_vortex_distribution(geometry, settings)[source]#
- Compute the coordinates of panels, vortices , control points
and geometry used to build the influence coefficient matrix. A different discretization (n_sw and n_cw) may be defined for each type of major section (wings and fuselages).
Control surfaces are modelled as wings, but adapt their panel density to that of the area in which they reside on their own wing.
Assumptions: Below is a schematic of the coordinates of an arbitrary panel
- XA1 ____________________________ XB1
- bound vortex |
- XAH| ________________________ |XBH
- | XCH | || | || | || | || | || 0 <–control | || XC point | || | |
- XA2 |_|________________________|_|XB2
- In addition, all control surfaces should be appended directly
to the wing, not the wing segments
For control surfaces, “positve” deflection corresponds to the RH rule where the axis of rotation is the OUTBOARD-pointing hinge vector symmetry: the LH rule is applied to the reflected surface for non-ailerons. Ailerons follow a RH rule for both sides
Source: None
Inputs: geometry.wings [Unitless] settings.floating_point_precision [np.dtype]
Of the following settings, the user should define either the number_ atrributes or the wing_ and fuse_ attributes. settings.number_of_spanwise_vortices - a base number of vortices to be applied to both wings and fuselages settings.number_of_chordwise_vortices - a base number of vortices to be applied to both wings and fuselages settings.wing_spanwise_vortices - the number of vortices to be applied to only the wings settings.wing_chordwise_vortices - the number of vortices to be applied to only the wings settings.fuselage_spanwise_vortices - the number of vortices to be applied to only the fuslages settings.fuselage_chordwise_vortices - the number of vortices to be applied to only the fuselages
Outputs: VD - vehicle vortex distribution [Unitless]
Properties Used: N/A
- generate_wing_vortex_distribution(VD, wing, n_cw, n_sw, spc, precision)[source]#
This generates vortex distribution points for the given wing
Assumptions: The wing is segmented and was made or modified by make_VLM_wings()
For control surfaces, “positve” deflection corresponds to the RH rule where the axis of rotation is the OUTBOARD-pointing hinge vector symmetry: the LH rule is applied to the reflected surface for non-ailerons. Ailerons follow a RH rule for both sides
The hinge_vector will only ever be calcualted on the first strip of any control/all-moving surface. It is assumed that all control surfaces are trapezoids, thus needing only one hinge, and that all all-moving surfaces have exactly one point of rotation.
Source: None
Inputs: VD - vortex distribution wing - a Data object made or modified by make_VLM_wings() to mimick a Wing object
Properties Used: N/A
- generate_fuselage_and_nacelle_vortex_distribution(VD, fus, n_cw, n_sw, precision, model_geometry=False)[source]#
This generates the vortex distribution points on a fuselage or nacelle component Assumptions: If nacelle has segments defined, the mean width and height of the nacelle is used Source: None
Inputs: VD - vortex distribution
Properties Used: N/A