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diff --git a/api/flowunsteady-maneuver/index.html b/api/flowunsteady-maneuver/index.html
diff --git a/api/flowunsteady-monitor/index.html b/api/flowunsteady-monitor/index.html
diff --git a/api/flowunsteady-openvsp/index.html b/api/flowunsteady-openvsp/index.html
diff --git a/api/flowunsteady-postprocessing-fdom/index.html b/api/flowunsteady-postprocessing-fdom/index.html
diff --git a/api/flowunsteady-postprocessing-misc/index.html b/api/flowunsteady-postprocessing-misc/index.html
diff --git a/api/flowunsteady-postprocessing-noise/index.html b/api/flowunsteady-postprocessing-noise/index.html
diff --git a/api/flowunsteady-run/index.html b/api/flowunsteady-run/index.html
diff --git a/api/flowunsteady-simulation/index.html b/api/flowunsteady-simulation/index.html
diff --git a/api/flowunsteady-vehicle-asm/index.html b/api/flowunsteady-vehicle-asm/index.html
diff --git a/api/flowunsteady-vehicle-components/index.html b/api/flowunsteady-vehicle-components/index.html
diff --git a/api/flowunsteady-vehicle-types/index.html b/api/flowunsteady-vehicle-types/index.html
diff --git a/api/flowvpm-particle/index.html b/api/flowvpm-particle/index.html
diff --git a/api/flowvpm-relaxation/index.html b/api/flowvpm-relaxation/index.html
diff --git a/api/flowvpm-sfs/index.html b/api/flowvpm-sfs/index.html
diff --git a/api/flowvpm-time/index.html b/api/flowvpm-time/index.html
diff --git a/api/flowvpm-uj/index.html b/api/flowvpm-uj/index.html
diff --git a/api/flowvpm-utils/index.html b/api/flowvpm-utils/index.html
diff --git a/api/flowvpm-viscous/index.html b/api/flowvpm-viscous/index.html
diff --git a/assets/themes/documenter-dark.css b/assets/themes/documenter-dark.css
diff --git a/assets/themes/documenter-light.css b/assets/themes/documenter-light.css
diff --git a/examples/blownwing-acoustics/index.html b/examples/blownwing-acoustics/index.html
diff --git a/examples/blownwing-aero/index.html b/examples/blownwing-aero/index.html
diff --git a/examples/blownwing-asm/index.html b/examples/blownwing-asm/index.html
diff --git a/examples/heavingwing/index.html b/examples/heavingwing/index.html
diff --git a/examples/openvsp-aircraft/index.html b/examples/openvsp-aircraft/index.html
diff --git a/examples/propeller-J040/index.html b/examples/propeller-J040/index.html
diff --git a/examples/propeller-incidence/index.html b/examples/propeller-incidence/index.html
diff --git a/examples/propeller-jsweep/index.html b/examples/propeller-jsweep/index.html
diff --git a/examples/propeller-quasisteady/index.html b/examples/propeller-quasisteady/index.html
diff --git a/examples/prowim-aero/index.html b/examples/prowim-aero/index.html
diff --git a/examples/rotorhover-acoustics/index.html b/examples/rotorhover-acoustics/index.html
diff --git a/examples/rotorhover-aero/index.html b/examples/rotorhover-aero/index.html
diff --git a/examples/rotorhover-fdom/index.html b/examples/rotorhover-fdom/index.html
diff --git a/examples/rotorhover-quasisteady/index.html b/examples/rotorhover-quasisteady/index.html
diff --git a/examples/tetheredwing/index.html b/examples/tetheredwing/index.html
diff --git a/examples/vahana-maneuver/index.html b/examples/vahana-maneuver/index.html
diff --git a/examples/vahana-monitor/index.html b/examples/vahana-monitor/index.html
diff --git a/examples/vahana-run/index.html b/examples/vahana-run/index.html
diff --git a/examples/vahana-vehicle/index.html b/examples/vahana-vehicle/index.html
diff --git a/examples/wing-4p2aoa/index.html b/examples/wing-4p2aoa/index.html
diff --git a/examples/wing-aoasweep/index.html b/examples/wing-aoasweep/index.html
diff --git a/generate_examples.jl b/generate_examples.jl
@@ -9,5 +9,4 @@ include("generate_examples_heaving.jl")
 include("generate_examples_propeller.jl")
 include("generate_examples_rotorhover.jl")
 include("generate_examples_blownwing.jl")
-include("generate_examples_prowim.jl")
 include("generate_examples_vahana.jl")
diff --git a/generate_examples_blownwing.jl b/generate_examples_blownwing.jl
@@ -8,7 +8,7 @@ remote_url = "https://edoalvar2.groups.et.byu.net/public/FLOWUnsteady/"
 open(joinpath(output_path, output_name*"-aero.md"), "w") do fout
 
  println(fout, """
- # [Wing-on-Prop Interactions](@id blownwingaero)
+ # [Aerodynamic Solution](@id blownwingaero)
 
  ```@raw html
  <div style="position:relative;padding-top:50%;">
@@ -20,17 +20,6 @@ open(joinpath(output_path, output_name*"-aero.md"), "w") do fout
  </div>
  ```
 
- In this example we show mount propellers on a swept wing.
- The wing is modeled using the actuator line model that represents the wing
- as a lifting line.
- This wing model is accurate for capturing wing-on-prop interactions.
- For instance, the rotor will experience an unsteady blade loading (and
- increased tonal noise) caused by the turning of the flow ahead of the wing
- leading edge.
- However, this simple wing model is not adecuate for capturing
- prop-on-wing interactions (see [the next two sections](@ref asm) to
- accurately predict prop-on-wing interactions).
-
  """)
 
  println(fout, "```julia")
@@ -170,17 +159,13 @@ open(joinpath(output_path, output_name*"-asm.md"), "w") do fout
  The ALM is very accurate for isolated wings and even cases with mild wake
  interactions.
  However, for cases with stronger wake interactions (e.g., a wake directly
- impinging on the wing surface), the ALM can lead to unphysical results as
- the flow tends to cross the airfoil centerline.
- To address this, we have developed an actuator surface model
- (ASM) to embed the wing surface in the LES domain and better
- represent the physics.
-
- The ASM spreads the surface vorticity following a pressure-like
- distribution.
- This produces a velocity field at the wing surface that minimizes the mass
- flow that crosses the airfoil centerline, thus better representing a solid
- surface:
+ impinging on the wing surface), we have developed an actuator surface model
+ (ASM) that introduces the surface vorticity into the LES domain that better
+ represents the physics.
+ This is done by spreading the surface vorticity following a pressure-like
+ distribution, which ends up producing a velocity field at the wing surface
+ that minimizes the flow that crosses the airfoil centerline, thus better
+ representing a solid surface:
 
  ```@raw html
  <center>
@@ -189,22 +174,16 @@ open(joinpath(output_path, output_name*"-asm.md"), "w") do fout
  </center>
  <br>
  ```
- For an in-depth discussion of the actuator models implemented in
- FLOWUnsteady, see Chapter 6 in
- [Alvarez' Dissertation](https://scholarsarchive.byu.edu/etd/9589)[^2]
- (also published in
- [Alvarez & Ning, 2023](https://arc.aiaa.org/doi/abs/10.2514/1.C037279)[^3]).
+ For an in-depth discussion of the actuator line and surface models
+ implemented in FLOWUnsteady, see Chapter 6 in
+ [Alvarez' Dissertation](https://scholarsarchive.byu.edu/etd/9589).[^2]
 
 
  [^2]: E. J. Alvarez (2022), "Reformulated Vortex Particle Method and
  Meshless Large Eddy Simulation of Multirotor Aircraft," *Doctoral
  Dissertation, Brigham Young University*.
  [**[VIDEO]**](https://www.nas.nasa.gov/pubs/ams/2022/08-09-22.html)
  [**[PDF]**](https://scholarsarchive.byu.edu/etd/9589/)
- [^3]: E. J. Alvarez and A. Ning (2023), "Meshless Large-Eddy Simulation of
- Propeller–Wing Interactions with Reformulated Vortex Particle Method,"
- *Journal of Aircraft*.
- [**[DOI]**](https://arc.aiaa.org/doi/abs/10.2514/1.C037279)[**[PDF]**](https://scholarsarchive.byu.edu/facpub/6902/)
 
  In order to activate the actuator surface model, we define the following
  parameters:
@@ -237,7 +216,7 @@ open(joinpath(output_path, output_name*"-asm.md"), "w") do fout
  add_unsteadyforce = false # Whether to add the unsteady force to Ftot or to simply output it
 
  include_parasiticdrag = true # Include parasitic-drag force
- add_skinfriction = true # If false, the parasitic drag is purely form, meaning no skin friction
+ add_skinfriction = true # If false, the parasitic drag is purely parasitic, meaning no skin friction
  calc_cd_from_cl = false # Whether to calculate cd from cl or effective AOA
  wing_polar_file = "xf-rae101-il-1000000.csv" # Airfoil polar for parasitic drag
  ```
@@ -251,7 +230,7 @@ open(joinpath(output_path, output_name*"-asm.md"), "w") do fout
  forces = []
 
  # Calculate Kutta-Joukowski force
- kuttajoukowski = uns.generate_aerodynamicforce_kuttajoukowski(KJforce_type,
+ kuttajoukowski = uns.generate_calc_aerodynamicforce_kuttajoukowski(KJforce_type,
  sigma_vlm_surf, sigma_rotor_surf,
  vlm_vortexsheet, vlm_vortexsheet_overlap,
  vlm_vortexsheet_distribution,
@@ -336,10 +315,12 @@ open(joinpath(output_path, output_name*"-asm.md"), "w") do fout
  )
  ```
 
- !!! info "ASM Example"
- The [next section](@ref prowimaero) shows an example on how to
- set up and run a simulation using the actuator surface model.
-
+ !!! info "ASM and High Fidelity"
+ ASM uses a very high density of particles at the wing
+ surface (~100k particles per wing) to accuratelly introduce the solid
+ boundary into the LES.
+ This increases the computational cost of the simulation considerably.
+ Hence, we recommend using ASM only for high-fidelity simulations.
  """)
 
 end
diff --git a/generate_examples_prowim.jl b/generate_examples_prowim.jl