-
+
- diff --git a/_tutorials/compressible_flow/Aachen_Turbine/Aachen_Turbine.md b/_tutorials/compressible_flow/Aachen_Turbine/Aachen_Turbine.md index c59324f2..7c8cd551 100644 --- a/_tutorials/compressible_flow/Aachen_Turbine/Aachen_Turbine.md +++ b/_tutorials/compressible_flow/Aachen_Turbine/Aachen_Turbine.md @@ -12,7 +12,7 @@ complexity: advanced follows: compressible flow tutorials --- - + ## Goals Upon completing this tutorial, the user will become familiar with 3D steady-state RANS calculations of multi-row axial turbines, elaborating viscous, compressible flows of air, modelled as an ideal gas. @@ -72,8 +72,8 @@ This tutorial will solve the flow through the Aachen turbine for the following b To reduce the computational cost, the geometrical periodicity of the system is exploited reducing the computational domain to one blade passage per row (with the blade at the centre of the mesh). As it will be explained later, this requires the use of periodic boundary conditions. - - + + Figure (1): Computational domain reduction. ### Mesh Description @@ -94,7 +94,7 @@ CONFIG_LIST=(stator1.cfg, rotor.cfg, stator2.cfg) #### Sub-config Files The most important information that must be specified in the sub-config files concerns the grid movement. To activate it, the `GRID_MOVEMENT` option must be specified, together with the `MOTION_ORIGIN` and angular velocity (`ROTATION_RATE`) components about the rotation axis.\ For the solver initialization the motion Mach number is specified via the `MACH_MOTION`. \ -Finally, a smoother convergence can be achieved via the `RAMP_ROTATING_FRAME`. Although not used in the present case, it can be activated similarly to the outlet pressure ramp, describe later in this tutorial. +Finally, a smoother convergence can be achieved via the `RAMP_MOTION_FRAME`. Although not used in the present case, it can be activated similarly to the outlet pressure ramp, describe later in this tutorial. These options are shown for the rotor sub-config file in the following box. @@ -109,13 +109,13 @@ MOTION_ORIGIN= 0.0 0.0 0.0 % Angular velocity vector in rad/s ROTATION_RATE= 0.0 0.0 -366.52 -RAMP_ROTATING_FRAME= NO +RAMP_MOTION_FRAME= NO % Parameters of the rotating frame ramp: starting rotational speed, updating-iteration-frequency, total number of iterations for the ramp -RAMP_ROTATING_FRAME_COEFF= (0.0, 150.0, 2000) +RAMP_MOTION_FRAME_COEFF= (0.0, 150.0, 2000) ``` ### Boundary Conditions @@ -132,7 +132,7 @@ The following box shows the syntax to be used to enforce this boundary condition MARKER_HEATFLUX = (BLADE1, 0.0, BLADE2, 0.0, BLADE3, 0.0, HUB1, 0.0, SHROUD1, 0.0, HUB2, 0.0, SHROUD2, 0.0, HUB3, 0.0, SHROUD3, 0.0) ``` - + Figure (2): Hub, shroud and blade surfaces. @@ -148,7 +148,7 @@ The following box shows the syntax to be used to enforce this boundary condition MARKER_PERIODIC = (PER1_STATOR1, PER2_STATOR1, 0.0, 0.0, 0.0, 0.0, 0.0, 8.7804878, 0.0, 0.0, 0.0, PER1_ROTOR, PER2_ROTOR, 0.0, 0.0, 0.0, 0.0, 0.0, 8.7804878, 0.0, 0.0, 0.0, PER1_STATOR2, PER2_STATOR2, 0.0, 0.0, 0.0, 0.0, 0.0, 8.7804878, 0.0, 0.0, 0.0) ``` - + Figure (3): Periodic and donor surfaces. #### Non-reflective boundary conditions @@ -177,7 +177,7 @@ The following box presents the corresponding syntax. 0.0, 0.0, 0.0, 0.0 , 1.0, 0.0) ``` - + Figure (4): Non-reflective inlet and outlet boundary conditions ###### Mixing-plane surfaces @@ -213,7 +213,7 @@ To make the mixing-plane turbulent, the following option must be used: TURBULENT_MIXINGPLANE= YES ``` - + Figure (5): Non-reflective mixing-plane To turn on the non-reflective behaviour, the `SPATIAL_FOURIER` should be set to `YES`. However, for the current tutorial it is not activated, as in the following box. @@ -225,7 +225,7 @@ If needed, extra under relaxation factor for the Giles BC at the hub and shroud GILES_EXTRA_RELAXFACTOR = (0.05, 0.05) ``` -Finally, the kind of average process for linearizing the Navier-Stokes equation at inflow and outflow boundaries, including mixing-plane(s), can be controlled by ```AVERAGE_PROCESS_KIND```. Possible options are: ```ALGEBRAIC```, ```AREA```, ```MASSSFLUX```, ```MIXEDOUT```. The default one is ```AREA```, however, only the ```MIXEDOUT``` option guarantees that the mixing plane treatment is conservative.\ +Finally, the kind of average process for linearizing the Navier-Stokes equation at inflow and outflow boundaries, including mixing-plane(s), can be controlled by ```AVERAGE_PROCESS_KIND```. Possible options are: ```ALGEBRAIC```, ```AREA```, ```MASSFLUX```, ```MIXEDOUT```. The default one is ```AREA```, however, only the ```MIXEDOUT``` option guarantees that the mixing plane treatment is conservative.\ The following box shows the setting to be used for the current case. ``` @@ -241,7 +241,7 @@ The following box shows the syntax to enforce this functionality. MARKER_SHROUD = (SHROUD1, SHROUD2, SHROUD3) ``` - + Figure (6): Shroud boundary condition #### Wall functions @@ -271,15 +271,15 @@ WALLMODEL_RELFAC= 0.5 #### Ramps -To ease the convergence of turbomachinery cases, particularly when the pressure ratio of the machine is large, the use of ramps can be beneficial. These can be applied to both rotational speed and outlet pressure via ```RAMP_OUTLET_PRESSURE``` and ```RAMP_ROTATING_FRAME```. \ +To ease the convergence of turbomachinery cases, particularly when the pressure ratio of the machine is large, the use of ramps can be beneficial. These can be applied to both rotational speed and outlet pressure via ```RAMP_OUTLET``` and ```RAMP_MOTION_FRAME```. \ For the sake of completeness, the use of the outlet pressure ramp is demonstrated presenting in the following box the syntax to activate it. ``` % Specify ramp option for Outlet pressure (YES, NO) default NO -RAMP_OUTLET_PRESSURE= YES +RAMP_OUTLET= YES % % Parameters of the outlet pressure ramp (starting outlet pressure, updating-iteration-frequency, total number of iteration for the ramp) -RAMP_OUTLET_PRESSURE_COEFF= (140000.0, 150.0, 2000) +RAMP_OUTLET_COEFF= (140000.0, 150.0, 2000) ``` @@ -290,7 +290,7 @@ To have SU2_CFD computing the typical turbomachinery performance indexes, the tu Additionally, the inlet and outlet boundary to each zone must be specified in stream-wise order via the ```MARKER_TURBOMACHINERY```, as well as the inlet and the outlet boundaries of the full machine via the ```MARKER_ANALYZE```. -Finally, the performance averaging method, i.e. AREA, MASSSFLUX, MIXEDOUT, etc., must be specified via the ```PERFORMANCE_AVERAGE_PROCESS_KIND```. In case the MIXEDOUT option is selected, the parameters for the Newton method used for the mixed out process can be specified via ```MIXEDOUT_COEFF```. +Finally, the performance averaging method, i.e. AREA, MASSFLUX, MIXEDOUT, etc., must be specified via the ```PERFORMANCE_AVERAGE_PROCESS_KIND```. In case the MIXEDOUT option is selected, the parameters for the Newton method used for the mixed out process can be specified via ```MIXEDOUT_COEFF```. The following box summarizes the setup for the Turbo Performance and Analysis of the current case. @@ -306,7 +306,7 @@ MARKER_TURBOMACHINERY= (INFLOW_STATOR1, OUTFLOW_STATOR1, MARKER_ANALYZE = (INFLOW_STATOR1, OUTFLOW_STATOR2) -% (ALGEBRAIC, AREA, MASSSFLUX, MIXEDOUT) default AREA +% (ALGEBRAIC, AREA, MASSFLUX, MIXEDOUT) default AREA PERFORMANCE_AVERAGE_PROCESS_KIND= MIXEDOUT %Parameters of the Newton method for the MIXEDOUT average algorithm (under relaxation factor, tolerance, max number of iterations) @@ -387,6 +387,6 @@ To compute it the following steps can be take in a post-processing tool, such as 4. Plot the relative Mach number contour of the extracted slice in a 2D space $(R \cdot \theta$ vs $z)$ and reverse the Z-axis, Fig. 7b. - - + + Figure (7): (a) Relative Mach number contour on a cylindrical cut (blade-to-blade view) at midspan of the turbine flow domain; (b) planar (blade-to-blade) view of the cylindrical cut. diff --git a/_tutorials/compressible_flow/ActuatorDisk_VariableLoad/ActuatorDisk_VariableLoad.md b/_tutorials/compressible_flow/ActuatorDisk_VariableLoad/ActuatorDisk_VariableLoad.md index c1f7c967..a9ccb282 100644 --- a/_tutorials/compressible_flow/ActuatorDisk_VariableLoad/ActuatorDisk_VariableLoad.md +++ b/_tutorials/compressible_flow/ActuatorDisk_VariableLoad/ActuatorDisk_VariableLoad.md @@ -12,7 +12,7 @@ complexity: Basic follows: --- - + ## Goals @@ -67,16 +67,16 @@ Three boundary conditions are employed: - Navier-Stokes adiabatic wall on the spinner. - Far-field condition on the outer domain surface. - + Figure (1): Far-field view of the computational domain. - + Figure (2): Mesh of the domain in the *x-y* plane. - + Figure (3): Close-up view of the mesh of the actuator disk in the *y-z* plane at *x=0*. - + Figure (4): Close-up view of the mesh of the spinner in the *y-x* plane. ### Configuration File Options @@ -182,10 +182,10 @@ These coefficients are defined using the "Renard" definition: the reference forc The visualization of the tabular input for this case is shown in the following figure: - + Figure (5): Thrust coefficient distribution along the non-dimensional radius. - + Figure (6): Power coefficient distribution along the non-dimensional radius. ### Optimal Propeller Script @@ -233,26 +233,26 @@ The actuator disk with variable load test case is small and will execute relativ Some results for this test case are shown below. - + Figure (7): Mach number contour in the *x-z* plane. - + Figure (8): Pressure coefficient contour in the *x-z* plane. - + Figure (9): Tangential velocity vectors just downstream the actuator disk. Swirl effect visualization. - + Figure (10): Momentum in normal direction along *x* for different stations. - + Figure (11): Pressure coefficient along *x* for different stations. - + Figure (12): Tangential velocity component along *x* for different stations. - + Figure (13): Pressure coefficient jump along the non-dimensional radius. - + Figure (14): Tangential velocity component along *z* just upstream (State 1) and downstream (State 2) the actuator disk. diff --git a/_tutorials/compressible_flow/NICFD_nozzle/NICFD_nozzle.md b/_tutorials/compressible_flow/NICFD_nozzle/NICFD_nozzle.md index daa72054..a5fbbab5 100644 --- a/_tutorials/compressible_flow/NICFD_nozzle/NICFD_nozzle.md +++ b/_tutorials/compressible_flow/NICFD_nozzle/NICFD_nozzle.md @@ -128,7 +128,7 @@ CRITICAL_PRESSURE= 1437500 ACENTRIC_FACTOR= 0.524 ``` -In addition, the models for transport coefficients can also be customized by exploring the viscosity and thermal conductivity options. By default with compressible flow, the laminar viscosity is governed by Sutherland’s law, and the thermal conductivity is assumed to depend on a constant Prandtl number. However, in the case of the Peng-Robinson-Stryjek-Vera equation of state (`PR_GAS`), the `CONSTANT_VISCOSITY` and `CONSTANT_CONDUCTIVITY` options are the only available. The values of the dynamic viscosity and thermal conductivity are imposed by entering the values for `MU_CONSTANT` and `KT_CONSTANT`. +In addition, the models for transport coefficients can also be customized by exploring the viscosity and thermal conductivity options. By default with compressible flow, the laminar viscosity is governed by Sutherland’s law, and the thermal conductivity is assumed to depend on a constant Prandtl number. In this tutorial, constant values are used instead, with the `CONSTANT_VISCOSITY` and `CONSTANT_CONDUCTIVITY` options. The values of the dynamic viscosity and thermal conductivity are imposed by entering the values for `MU_CONSTANT` and `THERMAL_CONDUCTIVITY_CONSTANT`. ``` % --------------------------- VISCOSITY MODEL ---------------------------------% @@ -146,7 +146,7 @@ MU_CONSTANT= 1.21409E-05 CONDUCTIVITY_MODEL= CONSTANT_CONDUCTIVITY % % Molecular Thermal Conductivity that would be constant (0.0257 by default) -KT_CONSTANT= 0.030542828 +THERMAL_CONDUCTIVITY_CONSTANT= 0.030542828 ``` Characteristics-based Riemann boundary conditions are imposed on the INFLOW and OUTFLOW boundaries. @@ -166,7 +166,7 @@ The parameters specified in the config excerpt below are: MARKER_RIEMANN= ( INFLOW, TOTAL_CONDITIONS_PT, 904388, 542.13, 1.0, 0.0, 0.0, OUTFLOW, STATIC_PRESSURE, 200000, 0.0, 0.0, 0.0, 0.0 ) ``` -In this test case, CFL adaptation is employed to accelerate convergence to steady state. Within this procedure, the CFL value at each iteration is determined based on the residual value at the current and previous iteration, as *CFL = CFL * (residual_old / residual_new)^power*. The value of *power* is given by the parameters `factor down` or `factor up` provided at the entry `CFL_ADAPT_PARAM`. The value of *power* is chosen depending on whether *residual_new* is greater or lower than the *residual_old*. The user can choose to only increase the CFL by setting the first entry of `CFL_ADAPT_PARAM` to `0`. +In this test case, CFL adaptation is employed to accelerate convergence to steady state. Within this procedure, the local CFL value is multiplied by a factor at each iteration. It is multiplied by `factor up` when the full solution update is applied and the linear solver converges well. It is multiplied by `factor down` when the update has to be strongly under-relaxed, when the linear solver does not converge well, or when the residuals oscillate. Otherwise the CFL value is kept. Both factors are given in `CFL_ADAPT_PARAM`, and the CFL value always stays between `CFL min value` and `CFL max value`. ``` % CFL number (initial value for the adaptive CFL number) diff --git a/_tutorials/compressible_flow/NICFD_nozzle/NICFD_nozzle_datadriven.md b/_tutorials/compressible_flow/NICFD_nozzle/NICFD_nozzle_datadriven.md index 6bac3dcf..33ea927f 100644 --- a/_tutorials/compressible_flow/NICFD_nozzle/NICFD_nozzle_datadriven.md +++ b/_tutorials/compressible_flow/NICFD_nozzle/NICFD_nozzle_datadriven.md @@ -102,9 +102,10 @@ The simulation us run by the following command ``` mpirun -n
+
+
+
+
+
diff --git a/search.json b/search.json
new file mode 100644
index 00000000..dd23f93e
--- /dev/null
+++ b/search.json
@@ -0,0 +1,8 @@
+---
+layout: null
+sitemap: false
+---
+[
+{% assign groups = "docs_v7,tutorials,vandv" | split: "," %}{% assign first = true %}{% for g in groups %}{% for doc in site[g] %}{% unless doc.title == nil %}{% unless first %},{% endunless %}{% assign first = false %}
+{"title": {{ doc.title | jsonify }}, "url": {{ doc.url | relative_url | jsonify }}, "section": {{ g | jsonify }}, "text": {{ doc.content | strip_html | normalize_whitespace | jsonify }}}{% endunless %}{% endfor %}{% endfor %}
+]
diff --git a/tools/test_search.js b/tools/test_search.js
new file mode 100644
index 00000000..81cdc740
--- /dev/null
+++ b/tools/test_search.js
@@ -0,0 +1,75 @@
+"use strict";
+
+const assert = require("node:assert/strict");
+const fs = require("node:fs");
+const path = require("node:path");
+const vm = require("node:vm");
+
+const html = fs.readFileSync(path.join(__dirname, "../search.html"), "utf8");
+const script = html.match(/Search
+Search the user guide, the tutorials and the V&V pages. All terms of two or more characters must appear on the page; shorter terms are ignored.
+ + + +