Switch to Ruff linting and formatting (#466)

* migrated local flake8 to ruff.toml

* add extend to ruff local configu

* whitespace fixes

* trigger checks

* Update ruff.toml configuration paths

* Update gitignore

* Automatic formatting changes

* Non-automatic fixes

* trigger build

* Trigger Build

* Formatting

---------

Co-authored-by: Alasdair Gray <alachris@umich.edu>

Author: kanekosh

.flake8

@@ -1,6 +1,9 @@
 # Ignore OpenMDAO reports folders
 **/reports/
 
+# pre-commit config file that should be manually copied from the mdolab/.github repo.
+.pre-commit-config.yaml
+
 *.pyc
 *.py~
 *.db

.gitignore

@@ -11,8 +11,7 @@ build:
   tools:
     python: "3.11"
 
-sphinx:
-  configuration: openaerostruct/docs/conf.py
+
 
 python:
   install:

.readthedocs.yaml

@@ -28,4 +28,4 @@ preferred-citation:
   number: "4"
   pages: "1815--1827"
   date: "2018-04"
-  doi: "10.1007/s00158-018-1912-8"
+  doi: "10.1007/s00158-018-1912-8"

CITATION.cff

@@ -23,7 +23,7 @@ def initialize(self):
             "compressible",
             types=bool,
             default=False,
-            desc="Turns on compressibility correction for moderate Mach number " "flows. Defaults to False.",
+            desc="Turns on compressibility correction for moderate Mach number flows. Defaults to False.",
         )
 
     def setup(self):

openaerostruct/aerodynamics/aero_groups.py

@@ -1,6 +1,7 @@
 """
 Class definition for CompressibleVLMStates.
 """
+
 import openmdao.api as om
 
 from openaerostruct.aerodynamics.get_vectors import GetVectors

openaerostruct/aerodynamics/compressible_states.py

@@ -11,7 +11,7 @@ class VLMGeometry(om.ExplicitComponent):
     Some of the quantities, like `normals`, are used to compute the RHS
     of the AIC linear system.
 
-    parameters
+    Parameters
     ----------
     def_mesh[nx, ny, 3] : numpy array
         Array defining the nodal coordinates of the lifting surface.

openaerostruct/aerodynamics/geometry.py

@@ -8,7 +8,7 @@ class LiftDrag(om.ExplicitComponent):
     Calculate total lift and drag in force units based on section forces.
     This is for one given lifting surface.
 
-    parameters
+    Parameters
     ----------
     sec_forces[nx-1, ny-1, 3] : numpy array
         Contains the sectional forces acting on each panel.

openaerostruct/aerodynamics/lift_drag.py

@@ -1,6 +1,7 @@
 """
 Class definition for the MeshPointForces component.
 """
+
 import numpy as np
 import openmdao.api as om
 

openaerostruct/aerodynamics/mesh_point_forces.py

@@ -4,7 +4,7 @@
 class TotalDrag(om.ExplicitComponent):
     """Calculate total drag in force units.
 
-    parameters
+    Parameters
     ----------
     CDi : float
         Induced coefficient of drag (CD) for the lifting surface.