PROWIM example and polish blown wing tutorial

byuflowlab · Jan 8, 2024 · 03187b8 · 03187b8
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diff --git a/docs/make.jl b/docs/make.jl
@@ -50,6 +50,7 @@ makedocs(
                                                         "examples/blownwing-aero.md",
                                                         # "examples/blownwing-acoustics.md",
                                                         "examples/blownwing-asm.md",
+                                                        "examples/prowim-aero.md",
                                                     ],
                                     "eVTOL Aircraft" => [
                                                         "examples/vahana-vehicle.md",

diff --git a/docs/src/api/flowunsteady-openvsp.md b/docs/src/api/flowunsteady-openvsp.md
@@ -1,4 +1,4 @@
-# [Importing OpenVSP geometry](@id openvsp_import)
+# [OpenVSP geometry](@id openvsp_import)
 
 ```@docs
 FLOWUnsteady.read_degengeom

diff --git a/docs/src/examples/blownwing-aero.md b/docs/src/examples/blownwing-aero.md
@@ -1,4 +1,4 @@
-# [Aerodynamic Solution](@id blownwingaero)
+# [Wing-on-Rotor Interactions](@id blownwingaero)
 
 ```@raw html
 <div style="position:relative;padding-top:50%;">
@@ -10,6 +10,17 @@
 </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).
+
 
 ```julia
 #=##############################################################################
@@ -199,8 +210,8 @@ for ri in 1:nrotors
 
     # Account for angle of attack of wing
     nrm = sqrt(x^2 + z^2)
-    x = nrm*cosd(AOAwing)
-    z = -nrm*sind(AOAwing)
+    x = (x==0 ? 1 : sign(x))*nrm*cosd(AOAwing)
+    z = -(z==0 ? 1 : sign(z))*nrm*sind(AOAwing)
 
     # Translate rotor to its position along wing
     O = [x, y, z]                                       # New position

diff --git a/docs/src/examples/blownwing-asm.md b/docs/src/examples/blownwing-asm.md
@@ -17,13 +17,17 @@ vorticity at the three-quarter chord, as shown here:
 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>
@@ -32,16 +36,22 @@ representing a solid surface:
 </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:
@@ -74,7 +84,7 @@ include_unsteadyforce       = true          # Include unsteady force
 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
 ```
@@ -88,7 +98,7 @@ that uses the vortex sheet:
 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,
@@ -173,10 +183,8 @@ uns.run_simulation( ...
                     )
 ```
 
-!!! 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.
+