## Pradtl Meyer Expansion Shock Simulation

OBJECTIVE

The objective of this study are followed as given below

1. Perform a literature review on the physics behind shock waves

2. Boundary conditions associate with shock waves

3. Study the effect of Sub-Grid-Scale (SGS) criteria on the Pradtl Meyer shock wave simulation results

Shock Waves:

Shock waves are high pressure wave trails generated around a sharped corner body traveling at supersonic velocity. Before the body reaches actual supersonic velocity, the air parcel flowing closely over the body surface reaches supersonic speeds due to which the shocks are generated. In other words the pressure, temperature and density of air changes abruptly at the local region when this occurs.

Based on the body geometry, the shock waves formed can be categorized as normal shock, oblique shock and bow shock/curved shock. Certian cases of two dimensional waves in supersonic flow shows opposite effect of oblique shock, such waves are called expansion waves in which the supersonic flow is turned away from itself. In these cases, the flow passes over the surface at an inclined angle w.r.t to the horizontal and all the flow steamlines are deflected downwards.The change in the flow direction and other parameters takes place across a fan centered at point A as shown below:

An expansion wave formed due to a sharp convex corner is known as centered expansion or Pradtl-Meyer expansion wave. Some of the key features of the PM expansion wave are:

1. The expansion takes place through a continuous succession of Mach waves which                  are isentropic in nature

2. The expansion of the flow takes place though an infinite number of Mach waves                    emitting from the center ‘A'

3. Smooth curved streamlines through the expansion wave

4. Static properties such as pressure,temperature and density decrease during the                         expansion process as the mach number increases

Boundary Conditions:

The Boundary conditions generally used for solving CFD problems are Neumann BC, Dirichlet BC and Mixed BC. For Pradtl Meyer expansion wave problem, Neumann and Dirichlet BC are used

Neumann BC: In case of Neumann boundary condition, the gradient of the variable () is specified at the boundary of the problem domain. Here, n is the direction, x, y, and z. One of the most frequently use Neumann boundary condition is the no flow boundary condition, i.e.  = 0 at the boundary

Dirichlet BC: For this type of boundary condition, the value of variable h(x,y,z,t) is specified at the boundary of the problem domain. This is also known as type I boundary condition. The head may be constant or may vary in space or in time.

Study of SGS criteria on Pradtl Meyer Shock Wave Simulation Results:

For studing this a transient state flow simulation is set up through a 2D channel with convex corner and various sgs values were used to understand the dependency of SGS parameter on the cell count along with shock location. The setup will be done for subsonic inlet velocity and supersonic inlet velocity to observe the formation of expansion fan. The following grid size and SGS criteria will be opted to setup the cases

Subsonic Inlet Velocity: 100m/s

Supersonic Inlet Veloctiy: 680m/s

 Grid Size Max. Embedding Level Sub-Grid Criteria Baseline dx=0.8m, dy=0.8m, dz=0.8m 2 0.05 Case 1 dx=0.8m, dy=0.8m, dz=0.8m 2 0.04 Case 2 dx=0.8m, dy=0.8m, dz=0.8m 2 0.03 Case 3 dx=0.8m, dy=0.8m, dz=0.8m 2 0.10

The simulation process includes three major steps:

1. Preprocessing

1.1. Geometry Import

1.2. Diagnosis

1.3. Boundary Flagging

1.4. Case Setup

2. Solving

3. Post Processing

3.1. Mesh

3.2. Plots (Density, Static Pressure, Mach Number)

3.3. Contours (Velocity, Static Pressure)

3.4. Animation (Velocity, Static Pressure)

PROCEDURE:

The procedure followed for setting up the simulation is provided below

1. Preprocessing

1.1. Geometry Import

a. The geometry provided was imported by dragging and dropping the file in the                        converge studio window

Fig. 1: Geometry (All dimension are in m)

1.2. Diagnosis: The diagnosis tool helps in identifying the different problems in the                    geometry.

The Diagnosis tool looks for the following geometric issues

a. Intersection: Highlights number of triangles with piercing inbetween adjacent two                 triangles

b. Nonmanifold Vertices: Checks for number vertex which are being shared between two           triangles

c. Open Edge: This highlights the number of edges of a triangle which not shared by any           other triangle

d. Normal Orientation: This highlights the number of traingles whose normal vector is               not pointing towards the interior of fluid domain

e. Isolated Triangles: This checks for the number of triangle surrounded by any                         neighbouring triangles that have different boundary ID number

Goto Diagnostics Dock>Find>

Since all the problem traingles are green ticked, there were no issues in the geometry

1.3. Boundary Flagging:

a. Goto Boundary>Flag>Create a New Boundary>Create Multiple Boundary>Enter 4 in               "Number of Multiple Boundaries" and the individual boundaries were renamed                       as: Inlet, Outlet, Front_2D, Back_2D and Slip

b. Selected the triangles at inlet and outlet, and applied to the respective boundaries.               Then the triangles in the Front and Back Walls were selected and applied to the                     respective boundaries. The same process was followed for the top and bottom walls               as well

The figure below represent the boundaries flagged

1.4. Case Setup:

a. Clicked on "Begin case Setup" and entered the value provided below

 Settings Values to be Entered Application General Flow Material Select Air (predefined mixture)Gas simulation>No ChangeGlobal Transport Paramters>No  ChangeReaction Mechanism> click on Import data from Mech.dat Simulation Parameters Run Paramters> Density-based steady solverSimulation Time Parameter>Start Time: 0End time: 15000 cyclesInitial time step: 1.0e-7 sMinimum time step: 1.0e-7 sMaximum time step: 1.0 sSolver Parameters> No Change Boundary Conditions Inlet> Boundary Type- INFLOW>Pressure Boundary Condition>Zero Normal Gradient (NE)Velocity Boundary Condition>Specified Value (DI)>Enter 100m/s as the value of velocity along x-direction, and assigned 0 for velocity in y and z directionTemperature Boundary Condition>286.1kSpecies Boundary Condition> AirOutlet>Boundary Type-OUTFLOW>Pressure Boundary Condition>Zero Normal Gradient (NE)Velocity Boundary Condition>Zero Normal Gradient (NE)Temperature Backflow>300kSpecies Backflow>AirFront_2D and Back_2D> Assign TWO_D for both the boundriesSlip>Boundary Type>Wall, Velocity Boundary Condition>Wall Type Motion>Stationary, Temperature Boundary Condition>Zero Normal Gradient (NE)Assign Region 0 to all the boundariesFor case 1,2 & 3 changed Vx=680m/s Initial Conditions & Events Regions and InitializationRegions and InitializationAdd region>"Region 0"Stream ID: 0Velocity: Vx=100m/s, Vy=Vz=0Temperature: 300kEnter Pressure value:500000PaSpecies: Add AirFor case 1,2 & 3 changed Vx=680m/s (Supersonic) Physical Models Turbulence Modeling-RNG-K Eplison is selected Grid Controls Enter the grid values for (dx, dy, dz) as per the case BaselineBaseline: dx = 0.8 m; dy = 0.8 m; dz = 0.8 mActivated Fixed Embedding from the menu Fixed Embedding-Add Embedding>AMR groups>tick on TemperatureSelect on the Avialable Region and click on => to shift the Region 0 to active regionsMax. Embedding Level>2Sub-Grid Criterion>0.05Timing Control Type:SequentialStart Time:5000 CyclesEnd Time: 9.99999e^9Similar Gird Size was used for Case 1, 2 & 3Case 1:Change Sub-Grid  Criterion>0.04Case 2:Change Sub-Grid  Criterion>0.03Case 3:Change Sub-Grid  Criterion>0.10 Output/Post Processing Post Variable Selection>No change Output Files Time Interval for writing 3D output data files: 1000 cycTime Interval for writing text output: 1.0 cycTime Interval for restarting output: 1000 cyc

After this all the input files was imported to a seperate folder. Converge creates .txt  files which contains all the values entered while setting up the case for respective settings done above. These input files will be processed by converge using Message Passing Interface (MPI) standard

2. Solving:

For running the simulation, Cygwin tool was used instead of converge studio interface. Cygwin is a POSIX-compatible API which is based on command prompt is used to run the simulation

Steps:

a. Navigated to the folder location containing the input files

b. Entered the command> mpiexec.exe -n 2 converge.exe logfile & : This allows converge to run two processors (selection on number of processor cores present as per the system configuration, can use multiple cores if available) for the parallel processing and load balancing

c. Entered the command> taif -f logfile

d. After the simulation is over. Went back to converge studio>Post-Processing 3D

e. Enter Case Name>"Test", Change the File Type to Paraview VTK in-line binary format

d. Enter the address for the output files>Select all files>Select all Cell Variables>click on Convert

e. After the conversion of the post files to the binary output, open the Test.vtm (group file) file in Paraview

3. Post-Processing:

After opening the group file in paraview, clicked on apply to load the results. Created slice, and other contour plots as required

3.1. Meshing:

Fig: Cell Count (Cases: Baseline, 1, 2 & 3)

Fig: Case 1: Mesh View

Fig: Case 2: Mesh View

Fig: Case 3: Mesh View

3.2. Plots

Density Plots

Fig: Baselinecase: Density Plots

Fig: Case 1: Density Plots

Fig: Case 2: Density Plots

Fig: Case 3: Density Plots

Static Pressure Plots

Fig:  Baselinecase: Static Pressure Plots

Fig:  Case 1: Static Pressure Plots

Fig:  Case 2: Static Pressure Plots

Fig:  Case 3: Static Pressure Plots

Mach Number Plots

Fig:  Baselinecase: Mach Number Plots

Fig :  Case 1: Mach Number Plots

Fig:  Case 2: Mach Number Plots

Fig:  Case 3: Mach Number Plots

3.3. Contours:

Fig: Velocity Contour (Baseline)

Fig: Pressure Contour (Baseline)

Fig: Velocity Contour (Case 1)

Fig: Pressure Contour (Case 1)

Fig: Velocity Contour (Case 2)

Fig: Pressure Contour (Case 2)

Fig: Velocity Contour (Case 3)

Fig: Pressure Contour (Case 3)

Case 1:Pressure

Case 1:Velocity

Case 1: Velocity with Surface with Edges

Case 2: Pressure with Surface with Edges

Case 2: Velocity with Surface with Edges

Case 3: Pressure with Surface with Edges

Case 3: Velocity with Surface with Edges

KEY CONCLUSIONS:

1. In the baseline case when the subsonic inlet velocity condition was used no change in the mesh count as the given SGS criteria was not fullfilled in the entire domain.

2. When the sub grid scale temperature change started at around 5000 cycles, the adaptive mesh refinement was observed.

3.In the supersonic flow, the effect of AMR based on temperature or velocity plays a very significant role in capturing physics. The SGS value should be kept low to capture the physics accurately; when the SGS parameter was provided was lowered in case 1 and 2, the formation of expansion fan was proper, but when increased in case 3, the formation of expansion fan was effected

4. Due to the formation of expansion shock, the static parameters such as pressure, density and temperature changed locally

5. Proper SGS value helps in understanding the point of shock generation on the boundary. For example, in case 1 velocity contour, the point of shock can be observed clearly as shown in the figure

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