Aerosandbox

- Fixed I/O error with AVL, where too many digits of precision would cause AVL to read .mass files incorrectly
- Added `asb.Opti.maximize()`, a convenience function that is a simple pass-through to `.minimize(-1 * x)`. Improves readability for users who are less familiar with optimization.
- Added support for the `keepdims` argument in aerosandbox.numpy.linalg.norm().
- Added optimization benchmarks in the tutorials, in `/tutorials/01 - Optimization and Math/01 - Optimization Benchmark Problems/`

- PENDING DEPRECATION added: `asb.Airplane.export_XFLR()` has been renamed to `asb.Airplane.export_XFLR5_xml()`. This clarifies that the output is an XFLR5 XML file (which needs to be imported through the Plane menu in XFLR5), not an XFLR5 .xfl file - a point of user confusion. For now, both will work, but the old name will trigger a warning, and eventually will be removed.
- Added improvements to `asb.LiftingLine` to ensure mixed-backend compatibility.

- Public release of `asb.NonlinearLiftingLine`, which is a new 3D aerodynamics analysis method implemented by Yashil Choony (yashil99) at Politecnico di Milano. It is implicitly solved (i.e., by iteration), subclassing `asb.ImplicitAnalysis`. This is a nonlinear lifting line theory method (with sweep and dihedral accounting), where the CL(alpha) function used to drive the nonlinear closure loop is taken from NeuralFoil. Fuselage influences can be optionally handled using a source-line (i.e. nonlifting) method. Preliminary testing on full-aircraft configurations indicates good agreement with other solvers, but production use should likely wait until more testing is performed in future versions.
- Added `asb.LiftingLine`, which is an experimental new 3D aerodynamics analysis method. It is explicitly solved by linearizing about the "naive" incidence angle on each surface, then doing a linear solve. Basic method is a lifting line theory method (with sweep and dihedral accounting), where the linearized sectional data is taken from NeuralFoil results for improved accuracy. Fuselage modeling is handled through a semi-empirical method (essentially, falling back on `asb.AeroBuildup`). Preliminary testing on full-aircraft configurations indicates good agreement with other solvers, but production use should likely wait until more testing is performed in future versions. Stability derivatives with respect to alpha and beta appear accurate, but rate derivatives (p, q, r) are not yet tested.
- Added save/load capabilities for AeroSandboxObjects (parent class of Airplane, Wing, Airfoil, etc.) via `AeroSandboxObject.save()` and `asb.load()`.

- Various plotting-related syntax changes to address deprecation warnings in Matplotlib 3.8.0.

- Added cost modeling capabilities for electric aircraft, in `aerosandbox.library.costs`.
- Rework of fuselage aerodynamics calculation to be much more accurate in moment prediction (and stability derivative prediction). This involves a much more precise moment integration based on slender body theory (potential flow around a line-source-doublet), and removing various unnecessary coordinate system conversions.
- Added deprecation warning on `/aerosandbox/geometry/airfoil/default_airfoil_aerodynamics.py`, which is superseded by `asb.Airfoil.get_aero_from_neuralfoil()`.
- BREAKING: In aircraft cost model (the DAPCA IV model in `/aerosandbox/library/costs.py`, adjusted key names on the dictionary output to be consistent with each other. This is a breaking change, but because this is a relatively new feature and buried very deep into the cost library, it's expected that this will affect very few users.

- Added `asb.KulfanAirfoil`, which is a new subclass of `asb.Airfoil` with the underlying parameterization as Kulfan (CST) parameters rather than a coordinate array. Useful for design optimization, as CST parameters can be optimized through, but raw coordinate arrays cannot.
- Added transonic airfoils from TASOPT to the AeroSandbox airfoil database. See them, for example, with `asb.Airfoil("tasopt-c090")`.
- Extend capabilities for `aerosandbox.numpy` functions `np.max`, `np.min`, `np.diag`.
- Added new tutorials on airfoil analysis and airfoil shape optimization. (Roughly in the path `/tutorials/Aerodynamics/...2D Aero Tools/NeuralFoil`)
- Begin work on a unified potential flow model for 3D aerodynamics, which will allow easy switching between different modeling assumptions.
- Added an improvement to Airplane geometry export to STEP thanks to Zcaic, which now makes a leading-edge line part of each Wing. Improves STEP accuracy.