RCAIDE.Library.Methods.Aerodynamics.Vortex_Lattice_Method.generate_vortex_distribution
generate_vortex_distribution#
- generate_aircraft_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
Outputs: VD - vehicle vortex distribution [Unitless]
Properties Used: N/A