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generate_examples.jl

@@ -9,4 +9,5 @@ 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")

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, """
-    # [Aerodynamic Solution](@id blownwingaero)
+    # [Wing-on-Rotor Interactions](@id blownwingaero)
 
     ```@raw html
     <div style="position:relative;padding-top:50%;">
@@ -20,6 +20,17 @@ 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-rotor 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
+    rotor-on-wing interactions (see [the next two sections](@ref asm) to
+    accurately predict rotor-on-wing interactions).
+
     """)
 
     println(fout, "```julia")
@@ -159,13 +170,17 @@ 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), 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:
+    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:
 
     ```@raw html
     <center>
@@ -174,16 +189,22 @@ open(joinpath(output_path, output_name*"-asm.md"), "w") do fout
     </center>
     <br>
     ```
-    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]
+    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]).
 
 
     [^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:
@@ -216,7 +237,7 @@ 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 parasitic, meaning no skin friction
+    add_skinfriction            = true          # If false, the parasitic drag is purely form, 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
     ```
@@ -230,7 +251,7 @@ open(joinpath(output_path, output_name*"-asm.md"), "w") do fout
     forces = []
 
     # Calculate Kutta-Joukowski force
-    kuttajoukowski = uns.generate_calc_aerodynamicforce_kuttajoukowski(KJforce_type,
+    kuttajoukowski = uns.generate_aerodynamicforce_kuttajoukowski(KJforce_type,
                                     sigma_vlm_surf, sigma_rotor_surf,
                                     vlm_vortexsheet, vlm_vortexsheet_overlap,
                                     vlm_vortexsheet_distribution,
@@ -315,12 +336,10 @@ open(joinpath(output_path, output_name*"-asm.md"), "w") do fout
                         )
     ```
 
-    !!! 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.
+    !!! 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.
+
     """)
 
 end

generate_examples_prowim.jl

@@ -0,0 +1,122 @@
+# ------------- BLOWN WING EXAMPLE ---------------------------------------------
+output_name = "prowim"
+example_path = joinpath(uns.examples_path, "prowim")
+
+remote_url = "https://edoalvar2.groups.et.byu.net/public/FLOWUnsteady/"
+
+# -------- Aero Solution --------------------------------------------------------
+open(joinpath(output_path, output_name*"-aero.md"), "w") do fout
+
+    println(fout, """
+    # [Rotor-on-Wing Interactions](@id prowimaero)
+
+    In this example we use the [actuator surface model](@ref asm) (ASM) to
+    accurately predict the effects of props blowing on a wing.
+    This case simulates the PROWIM experiment in
+    [Leo Veldhuis' dissertation](https://repository.tudelft.nl/islandora/object/uuid%3A8ffbde9c-b483-40de-90e0-97095202fbe3)
+    (2005), and reproduces the validation study published in
+    [Alvarez & Ning (2023)](https://arc.aiaa.org/doi/10.2514/1.C037279).
+
+    In this example you can vary the fidelity of the simulation setting the
+    following parameters:
+
+    | Parameter | Mid-low fidelity | Mid-high fidelity | High fidelity | Description |
+    | :-------: | :--------------: | :---------------: | :-----------: | :---------- |
+    | `n_wing` | `50` | `50` | `100` | Number of wing elements per semispan |
+    | `n_rotor` | `12` | `20` | `50` | Number of blade elements per blade |
+    | `nsteps_per_rev` | `36` | `36` | `72` | Time steps per revolution |
+    | `p_per_step` | `2` | `5` | `5` | Particle sheds per time step |
+    | `shed_starting` | `false` | `false` | `true` | Whether to shed starting vortex |
+    | `shed_unsteady` | `false` | `false` | `true` | Whether to shed vorticity from unsteady loading |
+    | `treat_wake` | `true` | `true` | `false` | Treat wake to avoid instabilities |
+    | `vlm_vortexsheet_overlap` | `2.125/10` | `2.125/10` | `2.125` | Particle overlap in ASM vortex sheet |
+    | `vpm_integration` | `vpm.euler` | RK3``^\\star`` | RK3``^\\star`` | VPM time integration scheme |
+    | `vpm_SFS` | None``^\\dag`` | Dynamic``^\\ddag`` | Dynamic``^\\ddag`` | VPM LES subfilter-scale model |
+
+    * ``^\\star``*RK3:* `vpm_integration = vpm.rungekutta3`
+    * ``^\\dag``*None:* `vpm_SFS = vpm.SFS_none`
+    * ``^\\ddag``*Dynamic:* `vpm_SFS = vpm.SFS_Cd_twolevel_nobackscatter`
+
+    (Mid-low fidelity settings may be inadequate for capturing rotor-on-wing interactions, unless using `p_per_step=5`)
+
+
+    """)
+
+    println(fout, "```julia")
+
+    open(joinpath(example_path, "prowim.jl"), "r") do fin
+
+        ignore = false
+
+        for l in eachline(fin)
+            if contains(l, "6) POSTPROCESSING")
+                break
+            end
+
+            # if l=="#=" || contains(l, "# Uncomment this")
+            if l=="#="
+                ignore=true
+            end
+
+            if !ignore && !contains(l, "save_code=")
+                println(fout, l)
+            end
+
+            if l=="=#" || contains(l, "# paraview      = false")
+                ignore=false
+            end
+        end
+    end
+
+    println(fout, "```")
+
+    println(fout, """
+    ```@raw html
+    <span style="font-size: 0.9em; color:gray;"><i>
+        Mid-low fidelity run time: 13 minutes a Dell Precision 7760 laptop. <br>
+        Mid-high fidelity run time: 70 minutes a Dell Precision 7760 laptop. <br>
+        High fidelity runtime: ~2 days on a 16-core AMD EPYC 7302 processor.
+    </i></span>
+    <br><br>
+    ```
+
+    ```@raw html
+    <center>
+        <br><br>
+        <b>Mid-High Fidelity</b>
+        <br>
+        <img src="$(remote_url)/prowimblown-compexp-midfi-composed.png" alt="Pic here" style="width: 100%;"/>
+        <br><br><br><br>
+        <b>High Fidelity</b>
+        <br>
+        <img src="$(remote_url)/prowimblown-compexp-hifi-composed.png" alt="Pic here" style="width: 100%;"/>
+        <br><br><br>
+    </center>
+    ```
+
+    The favorable comparison with the experiment at \$\\alpha=0^\\circ\$ and
+    \$4^\\circ\$ confirms that ASM accurately predicts propeller-wing
+    interactions up to a moderate angle of attack. At \$\\alpha=10^\\circ\$ we suspect
+    that the wing is mildly stalled, leading to a larger discrepancy (further
+    discussed in [Alvarez' Dissertation](https://scholarsarchive.byu.edu/etd/9589)[^1]
+    and
+    [Alvarez & Ning, 2023](https://arc.aiaa.org/doi/abs/10.2514/1.C037279)[^2]).
+
+    !!! info "Source file"
+        Full example available under
+        [examples/prowim/](https://github.com/byuflowlab/FLOWUnsteady/blob/master/examples/prowim).
+
+
+
+    [^1]: 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/)
+    [^2]: 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/)
+    """)
+
+end