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- Symmetry Considerations
- Aerodynamic Axes
- Surface Groups
- Euler and Navier-Stokes Equations
- Turbulence Models
- Gas Models
- Other Models
- Flowfield Initialization

Wind-US may be used with structured grids for axisymmetric, two-dimensional, or three-dimensional geometric configurations. Two-dimensional grids may be used not only for two-dimensional cases, but also for axisymmetric and area variation (quasi-three-dimensional) cases. Unstructured grids may be used only for three-dimensional configurations.

In three dimensions, each zone's computational mesh is comprised of six
boundary faces and an interior grid.
For structured grids, the mesh points are identified by three indices,
usually labeled (*i, j, k*).
In unstructured grids, each individual grid cell, and cell face, is
numbered.
Boundary conditions for each boundary face must be specified with
GMAN or
MADCAP
before the grid may be used with Wind-US.

Two-dimensional cases may be run using structured grids only.
The grid must be oriented such that the maximum *k*-index of the
grid is one.
In other words, a two-dimensional grid is defined by four boundary faces
and an interior grid labeled by *i*- and *j*-indices.
The grid must also reside in a non-zero, constant *z*-coordinate plane.
The actual value used will not affect solution convergence or flowfield
features, but it will affect flux-related post-processing calculations
such as mass flow.
For this reason, a value of 1.0 is recommended.
Boundary conditions for the four boundary lines must be specified in
GMAN or
MADCAP.

With structured grids, the effect of area variation on two-dimensional
computational models may be computed by using Wind-US's
"quasi-three-dimensional" capability, which is activated simply
through changes in the *z*-coordinate.
The value of the *z*-coordinate is the "width" of the field at each
grid point; the complete grid therefore represents the "width"
variation of the field as a function of *x* and *y*.
The important quantity to model is the ratio of cross-sectional areas
between two adjacent axial stations.
This means that the *z*-coordinate may be scaled with no effect on the
computed flowfield, but a simple translation of the *z*-coordinates will
change the computed flowfield, because the cross-sectional area ratio
will be different.
As with two-dimensional calculations, the value of the *z*-coordinate
will affect flux-related post-processing calculations.

Axisymmetric configurations may be modeled with structured grids, by
using a two-dimensional grid generated at an arbitrary circumferential
location on the geometry - e.g., the top centerline.
Note that the grid should be generated on only one "side" of
the configuration.
Once again, the *z*-coordinate of the grid should be 1.0.
The final step in using Wind-US's axisymmetric mode
is the specification of the symmetry axis location and the
circumferential sweep angle in the input data file.
The circumferential sweep angle is the angle of the "pie shape"
swept out by the grid about the symmetry axis.
Although the value of the sweep angle will not affect the computed
flowfield, it will affect flux-related post-processing calculations.

*Keywords:* `AXISYMMETRIC`

Aerodynamic axes may be specified to ease the set-up and post-processing
of CFD solutions, particularly when starting from a given CAD geometry
and orientation. These axes are defined by the "downstream", "up",
and "out" (or "side") directions as illustrated in the figure below.
The "downstream" direction specifies the vehicle axis and its orientation
from nose to tail. The "up" axis is used to orient the upper surface of
the vehicle. The "out" (or "side") axis is defined by the "downstream"
axis crossed with the "up" axis, however the "out" (or "side")
direction (±) may be specified independently and will be used
when computing the side forces.

The default set of aerodynamic axes is defined as follows: "downstream" (+x), "up" (+y), "out" (+z). To specify the aerodynamic axes with GPRO, select the following options.

C - Write Output File C - COMMON (cgd) File D - Modify aeroaxis in existing file Enter name of common file (grid.cgd) (This will open the grid file and display the current aerodynamic axes settings.) Downstream axis is +X Up axis is +Y Out axis is +Z Change the current aerodynamic axes? (y/n) Enter the downstream direction (+X,+Y,+Z,-X,-Y,-Z) Enter the up direction (+X,+Y,+Z,-X,-Y,-Z) Enter the side force direction (+X,+Y,+Z,-X,-Y,-Z) R - Return to main menu S - STOP GPROThe aerodynamic axes currently set within a grid file can be viewed using GPRO and are written to the top of the list output file (

Flow angles specified in the input data file (*.dat*) via the
`FREESTREAM`,
`ARBITRARY INFLOW`, or
`SYNTHETIC JET`
keywords are relative to the aerodynamic axes.
The angle of attack (α), defined in the plane formed by the
"downstream" and "up" directions, represents the "vertical" angle
between the freestream velocity and the vehicle axis. Negative, zero,
and positive α values correspond to nose down, level flight, and
nose up conditions respectively. In other words, positive α
yields flow with a +"up" component.
The angle of sideslip (β), defined in the direction
perpendicular to the plane formed by the "downstream" and "up"
directions (ie, "downstream" cross "up"), represents the "lateral"
angle between the freestream velocity and the vehicle axis. Negative,
zero, and positive β values correspond to the wind approaching
from the vehicle left, center, and right respectively. Note that the
± sign of the "out" axis direction has no bearing on the sign
of the sideslip angle, because β is always defined in the
direction formed from the "downstream" axis crossed with the "up" axis.
Flow angles for the
`ACTUATOR DISK` and
`BLEED`
keywords are always specified using geometry angles since they are
more closely tied to geometry than wind axes.

*Keywords:* `
FREESTREAM,
ARBITRARY INFLOW,
SYNTHETIC JET`

When computing integrated forces and moments via the
`LOADS` keyword:

- The drag force is in the direction of the freestream velocity (α, β).
- The lift force is perpendicular to drag and oriented towards the "up" direction (α+90, β=0). Only for α=0 will the lift force be exactly parallel to the "up" direction. Since the lift force is always contained in the plane formed by the "downstream" and "up" directions, it does not contain any force component in the "out" direction.
- The side force is perpendicular to both lift and drag (α, β±90), but with the sign determined based on user specification of the "out" (or "side") direction. Only for β=0 will the side force be parallel to the "out" direction.
- Moments are always computed in body axes, not aerodynamic axes.

Forces computed via the
`INTEGRATE FORCE`
keyword in CFPOST should be equivalent to those from the
`LOADS`
keyword above, since it reads the aerodynamic axes from the grid
file and implicitly issues the necessary
`ORIENTATION`
commands.

*Keywords:* `
LOADS`

Surface groups are used to reference a surface, or collection of surfaces,
which may extend across multiple zones. They offer several convenience
factors, including the ability to:
refer to named pieces of the geometry
(like wing, tail, nozzle, airplane, etc.),
use them in the flow solver for requesting
` LOAD` reports, and
use them in post-processing with CFPOST and some commercial software.
Surface groups can be defined using the CFPART utility.
It is usually easier to do this before splitting a grid into
multiple zones, simply because there are fewer surfaces to specify.
When CFPART is used to split a grid, it will propagate the surface
group definitions to the split grid.

Wind-US may be used to solve the Euler equations or the Reynolds-averaged form of the Navier-Stokes equations. [Bush, R. H. (1988) "A Three Dimensional Zonal Navier-Stokes Code for Subsonic Through Hypersonic Propulsion Flowfields," AIAA Paper 88-2830.] All heat transfer and stress tensor terms are retained, and the equations are modeled in full conservation form. The effects of turbulence may be modeled using a variety of algebraic, one-equation, and two-equation turbulence models. Modification of the effective heat transport coefficient due to turbulence is linked to the momentum diffusion coefficient by a turbulent Prandtl number, which is assumed to be constant.

The fluid may be treated as a thermally and calorically perfect gas, a
thermally perfect gas, equilibrium air, or a mixture undergoing a finite
rate chemical reaction.
For an ideal gas, conventional values are given to
the gas constant *R* and the ratio of specific heats *γ*,
or they may be specified.
Effects of gravity (i.e., stratification) and rotation may also be included.

The equation set(s) to be solved must be specified in the input data file.

*Keywords:* `
TURBULENCE,
GRAVITY,
ROTATE`

Freestream flowfield conditions - Mach number, pressure, temperature,
angle of attack, and angle of sideslip - must be specified in the
input data file.
The Mach number must be greater than zero, and pressure
and temperature may be specified as static or total values.
These conditions are used to initialize the flowfield at the start of a run.
For external flow problems, they are also applied at all inflow,
outflow, and freestream boundaries during the course of a flow solution.
For this reason, the outermost grid boundary should be far enough away
from the body such that the freestream assumption is valid at the boundary.

*Keywords:* `FREESTREAM`

The Reynolds number may be directly specified rather than the
freestream pressure. The input value should be the Reynolds
number based on the freestream velocity U and per unit grid
length. The freestream and reference information is written
to the top of the list output file so that you may confirm that
your input was interpreted correctly.

*Keywords:* `FREESTREAM`

Here are a couple of examples.

*Case I: Grid is same size as model*

Suppose we have the grid for a wind tunnel model, and we want to run
it at *M _{∞}* = 0.7 and a Reynolds number
of 12.1 million (based on the model length).
We arbitrarily choose a total temperature of
520 °R (static temperature of 473.6 °R).
Knowing the temperature, we can calculate
the speed of sound (

We now have the Mach number and temperature for the Wind-US input data file, but we still need to calculate the freestream pressure. Using the definition of the Reynolds number (and the ideal gas law),

or

Note that *Re _{L}* is the Reynolds number per unit length
of the physical model. For our example, if the model length is 10 inches,

We can now calculate *P*:

We would now like to check our input.
If we run Wind-US with the Mach, temperature and pressure specified above,
the code will print a Reynolds number and a reference length near
the top of the list output file.
*To obtain the desired Reynolds number, divide Wind-US's value of the
Reynolds number by the output reference length and multiply by the model body
length.
This number may be compared with the desired model Reynolds number.*

*Case II: Grid is scaled from model size*

Let us now assume that we want to run the previous grid at flight conditions, but we want to keep our same old 10-inch grid. We simply need to multiply the pressure by a scale factor. The equation now becomes:

where

For example, if we want to run a 100-inch wing using our 10-inch grid,
*S* = 10.
If we want to run a flight Reynolds number of 26 million,
we calculate *P* as:

One of the options available in Wind-US is the specification of mass flow boundary conditions for subsonic duct analyses. Actual or corrected mass flow may be specified at duct exits, as may back pressure.

Within Wind-US and many post-processors, routines exist which integrate mass flow at desired computational planes. For 3D cases, the desired mass flow may be compared directly with the output from the integration routines.

However, for 2D calculations, the comparison is not so straightforward. There are three cases to consider.

*Case I: 2D, Unit Depth*

The first case involves running Wind-US on a truly two-dimensional grid of
*unit depth* (*z*-coordinate is 1.0 everywhere).
In this case, the input mass flow should be *per unit depth*.
For example, let's say we want to run a 2D, unit depth model of a duct
with a square exit.
(If the exit were not square, this model would probably not be very good.)
We would like a corrected mass flow of 500 lb_{m}/sec,
and our actual model exit depth is 10 inches.
If the grid input units are inches, we should ask for a mass flow of
50 lb_{m}/sec.
If the grid input units are *not* inches, simply divide the actual
mass flow by the *z*-coordinate value *in inches*.

*Case II: 2D, Variable Width*

When the *z*-coordinate is the width of the 2D grid, Wind-US adds in the
area variation as a source to the 2D equations, making the analysis
quasi-three-dimensional.
In this case, the actual 3D mass flow should be specified in the input file.
The integrated exit area will be (approximately,
see the description of mass flow and grid areas)
the real duct exit area,
if the width has been specified correctly.

*Case III: 2D, Axisymmetric*

Axisymmetric runs require specification of the symmetry axis location
and the circumferential angle subtended by the 2D grid.
(This angle has no influence on the solution, but it does determine the area
perpendicular to the grid.)
The only reason this angle is an input parameter is so that you will
know what the streamwise area is.
In this case, the real exit geometry is circular, with a corresponding
mass flow.
The ratio of the input mass flow to the actual mass flow
should equal the ratio of the input circumferential angle to 360.
For example, if we are modeling a circular duct with a mass flow of
200 lb_{m}/sec using an axisymmetric model in Wind-US,
and if we specify a circumferential angle of 36 (1/10 of 360),
we should specify a mass flow of 20 lb_{m}/sec
(1/10 of 200 lb_{m}/sec).

*Keywords:* `MASS FLOW`,
`LOADS`

When dealing with subsonic duct analyses, you should be aware that the duct area as represented by the grid may be slightly different from the real area of the geometry being modeled, especially for ducts modeled with quasi-polar structured grids.

The duct area represented by the computational grid is often smaller than the real duct area, which, when running near critical mass flow, may prematurely choke the flow in the CFD solution. If the duct is circular and is modeled with a quasi-polar grid, the area error may be estimated.

Suppose we are modeling a circular duct with a quasi-polar grid using
*k _{max}* = 33 circumferential points, each of
which lie on the perimeter of the real duct at some streamwise station.
If the circumferential points are evenly distributed, we may describe
this topology as a circle which circumscribes a regular polygon of

which means that the "grid area" is

For our example, with

There is no need to worry about this difference for most cases, but you should be aware of its possible effects.

At solid walls, Wind-US uses an adiabatic heat transfer boundary condition by default. A constant wall temperature may also be specified in the input data file.

Through the use of the
`TTSPEC` keyword,
point-by-point wall temperature distributions may also be specifed
on boundary surfaces in structured grids.
An auxiliary code,
*tmptrn*,
is used to create the wall temperature distribution, and write it into
the common flow (*.cfl*) file.

The thermal conductivity is determined using a constant Prandtl number.

*Keywords:* `WALL TEMPERATURE,
TTSPEC`

By default, Wind-US uses Sutherland's law to define laminar viscosity as
a function of temperature.
Keye's formula may be used in addition to Sutherland's law, and
Wilke's law may be used to compute the laminar viscosity for
multi-species flows.

*Keywords:* `VISCOSITY`

For turbulent calculations, Reynolds averaging assumptions are used to define a turbulent (eddy) viscosity, which is added to the laminar viscosity in the flow calculations. All the turbulence models available in Wind-US are coupled to the Navier-Stokes equations only through the turbulent viscosity.

For structured grids, users have a choice of several algebraic, one-equation, and two-equation turbulence models. In addition, various combined RANS/LES models may be used. For unstructured grids, one-equation and two-equation models are available.

Note that a turbulence model (or inviscid or laminar flow) must be specified in the input data file. Wind-US will stop if you do not.

The algebraic turbulence models available in Wind-US for structured
grids are
the Cebeci-Smith model
*[Cebeci, T. (1970)
"Calculation of Compressible Turbulent Boundary Layers with Heat and MassTransfer,"
AIAA Paper 70-741]*,
the Baldwin-Lomax model
*[Baldwin, B. S., and Lomax, H. (1978)
"Thin Layer Approximation and Algebraic Model for Separated Turbulent Flows,"
AIAA Paper 78-257]*,
and the P. D. Thomas model
*[Thomas, P. D. (1979)
"Numerical Method for Predicting Flow Characteristics and Performance
of Nonaxisymmetric Nozzles - Theory,"
NASA CR 3147]*,
which adds a shear layer model to the Baldwin-Lomax model.
After each iteration of the flow solver, these models compute
the turbulent viscosity based on current flowfield quantities.
Note that, because of their dependence on maxima and minima of flowfield
variables, these models produce discontinuous turbulent viscosity
distributions in the computed flowfield and require special numerical
treatment at the juncture of two walls and on computational *i*-boundaries
(the latter for historical reasons).
The Baldwin-Lomax model is the most widely used algebraic
turbulence model in Wind-US.

*Keywords:* `TURBULENCE`

Because of their efficiency and ability to produce continuous turbulent
viscosity distributions, the one-equation turbulence models in Wind-US
are the models of choice for many engineering applications.
The one-equation models available in Wind-US for structured grids are the
Baldwin-Barth
*[Baldwin, B. S., and Barth, T. J. (1990)
"A One-Equation Turbulence Transport Model for High Reynolds Number
Wall-Bounded Flows,"
NASA TM 102847]*
and Spalart-Allmaras
*[Spalart, P. R., and Allmaras, S. R. (1992)
"A One-Equation Turbulence Model for Aerodynamic Flows,"
AIAA Paper 92-0439]*
models.
The one-equation models available for unstructured grids are that of
Spalart-Allmaras and the pointwise model of Goldberg
*[Goldberg, U. C., and Ramakrishnan, S. V. (1993)
"A Pointwise Version of the Baldwin-Barth Turbulence Model,"
AIAA Paper 1993-3523;
Goldberg, U. C. (1994)
"A Pointwise One-Equation Turbulence Model for Wall-Bounded
and Free Shear Flows,"
Proc. Int. Sym. Turb., Heat and Mass Trans.,
p.13.2.1, Lisben, Portugal]]*

*Keywords:* `TURBULENCE,
FREE_ANUT`

Several two-equation turbulence models are currently available in Wind-US.

- The Menter Shear Stress Transport (SST) model

*[Menter, F. R. (1993) "Zonal Two Equation**k*-*ω*Turbulence Models for Aerodynamic Flows," AIAA Paper 93-2906; Mani, M., Ladd, J. A., Cain, A. B., and Bush, R. H.(1997) "An Assessment of One- and Two-Equation Turbulence Models for Internal and External Flows," AIAA Paper 97-2010]

- The low-Reynolds-number Chien
*k*-*ε*model

*[Chien, K. Y. (1982) "Prediction of Channel and Boundary-Layer Flows with a Low-Reynolds-Number Turbulence Model," AIAA Journal, Vol. 20, No. 1, pp. 33-38]*

- The low-Reynolds-number Rumsey-Gatski
*k*-*ε*algebraic Reynolds stress model

*[Rumsey, C., Gatski, T., and Morrison, J. (1999) "Turbulence Model Predictions of Strongly Curved Flow in a U-Duct," AIAA Journal, Vol. 38, No. 8, pp.1394--1402; Rumsey, C. and Gatski, T. (2000) "Recent Turbulence Model Advances Applied to Multielement Airfoil Computations," Journal of Aircraft, Vol. 38, No. 5, pp. 904--910, Presented as AIAA Paper 2000-4323; Yoder, D. A. (2003) "Initial Evaluation of an Algebraic Reynolds Stress Model for Compressible Turbulent Shear Flows," AIAA-2003-0548]*

- The low-Reynolds-number realizable non-linear
*k*-*ε*model of Goldberg

*[Goldberg, U., Peroomian, O., and Chakravarthy, S. (1998) "A Wall-Distance-Free k-epsilon Model With Enhanced Near-Wall Treatment," Journal of Fluids Engineering, Vol. 120, Iss. 3, pp. 457-462; Goldberg, U. and Apsley, D. (1997) "A Wall-Distance-Free Low Re k-epsilon Turbulence Model," Computer Methods in Applied Mechanics and Engineering Vol. 145, Iss. 3-4, pp. 227-238]*

- The low-Reynolds number non-linear
*k*-*ε*model of Shih

*[Shih, T.-H., Liu, N.-S., and Chen, K.-H. (1998) "A Non-Linear k-epsilon Model for Turbulent Shear Flows," AIAA-1998-3983; Shih, T.-H. and Lumley, J. (1993) "Remarks on Turbulent Constitutive Relations," NASA TM-106116]*

The SST model may be used with both structured and unstructured grids.
Some of the *k*-*ε* models are available for structured
grids, while the others are only available for unstructured grids.

The Menter Shear Stress Transport (SST) model is a blend of
*k*-*ε* and *k*-*ω*.
The equations are cast in *k*-*ω* form.
Near viscous boundaries the *k*-*ω* model is used,
and the *k*-*ε* model is used away from walls
and in shear layers.
Each equation is solved individually and an iterative method
has been used on the implicit side to reduce the factorization error.
The model is robust, and may be more accurate in adverse pressure gradients
than some of the other models in Wind-US.
The SST model may be used with or without compressibility corrections, and
freestream values of *k* and *ω* may be specified.

The Chien *k*-*ε* model and
the Rumsey-Gatski *k*-*ε* algebraic Reynolds stress
model are available in Wind-US for use on structured grids.
Several options may be specified with these models to control the
initialization procedure, enhance stability, and improve accuracy in
adverse pressure gradients and at high Mach numbers.

The realizable *k*-*ε* model of Goldberg and
the Shih non-linear *k*-*ε* model
may be used with unstructured grids.

*Keywords:* `TURBULENCE,
COMPRESSIBLE DISSIPATION,
PRESSURE DILATATION,
FREE_K,
FREE_OM,
K-E keywords`

The idea behind combined RANS/LES (Reynolds-Averaged Navier Stokes / Large Eddy Simulation) turbulence models is to improve predictions of complex flows in a real-world engineering environment, by allowing the use of LES methods with grids typical of those used with traditional Reynolds Averaged Navier Stokes models. The combined model reduces to the standard RANS model in high mean shear regions (e.g., near viscous walls), where the grid is refined and has a large aspect ratio unsuitable for LES models. As the grid is traversed away from high mean shear regions, it typically becomes coarser and more isotropic, and the combined model smoothly transitions to an LES model.

Several combined RANS/LES models are available in Wind-US.

- The Spalart Detached Eddy Simulation (DES) model,
used in conjunction with the Spalart-Allmaras model.

*[Spalart, P. R., Jou, W. H., Strelets, M., and Allmaras, S. R. (1997) "Comments on the Feasibility of LES for Wings, And on a Hybrid RANS/LES Approach," First AFOSR International Conference On DNS/LES, Aug. 4--8, 1997, Ruston, Louisiana. In**Advances in DNS/LES*, Liu, C., and Liu, Z., eds., Greyden Press, Columbus, Ohio; Shur, M., Spalart, P. R., Strelets, M., and Travin, A. (1999) "Detached-Eddy Simulation of an Airfoil at High Angle of Attack," Fourth International Symposium on Engineering Turbulence Modeling and Measurements, May 24--26, 1999, Corsica]

- The Shih Modified DES (MDES) model,
used in conjunction with the Spalart-Allmaras model.

- The Spalart Delayed DES (DDES) model,
also used in conjunction with the Spalart-Allmaras model.

*[Spalart, P. R., Deck, S., Shur, M. L., Squires, K. D., Strelets, M., and Travin, A. (2006) "A New Version of Detached-Eddy Simulation, Resistant to Ambiguous Grid Densities," Theoretical and Computational Fluid Dynamics, Vol. 20, pp.181-195.]*

- The LESb model, which uses the SST model with a limiter on
*ε*.

*[Bush, R. H., and Mani, M. (2001), "A Two-Equation Large Eddy Stress Model for High Sub-Grid Shear," AIAA Paper 2001-2561]*

- The hybrid model of Nichols and Nelson, which may be used with
both the SST and the Chien
*k*-*ε*models.

*[Nichols, R. H., and Nelson, C. C. (2003) "Applications of RANS/LES Turbulence Models," AIAA Paper 2003-0083]*.

- The Partially Resolved Numerical Simulation (PRNS) method
and the Detached PRNS method
may also be used with the Spalart-Allmaras model.

*[Liu, N.-S., and Shih, T.-H. (2006) "Turbulence Modeling for Very Large-Eddy Simulation," AIAA Journal, Vol. 44, No. 4, pp. 687-697]**[Shih, T.-H., Liu, N.-S., and Chen, C.-L. (2006) "A Strategy for Very Large Eddy Simulation of Complex Turbulent Flows," AIAA Paper 2006-175]*

The combined models may only be used for unsteady flows (i.e., the time
step is a constant).
They are zonal, however, so you can use a combined model in time-accurate
mode in one zone, while using a standard RANS model in steady-state mode
in the other zones.

*Keywords:* `TURBULENCE,
DES,
MDES,
DDES,
LESB,
HYBRID,
PRNS,
DETACHED-PRNS`

Through the use of the
`TTSPEC` keyword,
point-by-point transition data may be specifed on viscous walls in
structured grids.
The data represent the percentage of turbulent
viscosity to be added to the laminar viscosity at each grid point.
An auxiliary code,
*tmptrn*,
may be used to create the transition data, and write it into
the common flow (*.cfl*) file.

*Keywords:* `TTSPEC`

A variety of gas models are available in Wind-US to complete the equation
set.
The fluid may be treated as a thermally and calorically perfect
gas, a thermally perfect gas (frozen chemistry), equilibrium air, or a
mixture undergoing a finite-rate chemical reaction.
Several different chemistry packages are available as files containing
thermodynamic data, reaction rate data, and transport property data.

*Keywords:* `CHEMISTRY`

For structured grids, various other models are available in Wind-US to model specific physical features of the geometry.

To simulate fan or compressor discontinuities, Wind-US provides an actuator
disk modeling capability, which acts as a modification to the zone coupling
boundary condition.
The model assumes an infinitesimally thin disk and must be applied at a
coupled zonal interface.
The actual discontinuity is specified in the input data file as a
solid-body rotation or free vortex flow, the effects of which are
applied when transferring flow information between the two specified
zone boundaries.

*Keywords:* `ACTUATOR`

Flowfield screens may also be modeled in Wind-US as discontinuities across
coupled zonal interfaces.
In the Wind-US input data file, one must specify the zones and boundaries
between which the screen is located, the solidity of the screen,
and one of several methods for calculating the losses through the screen.
The screen model is not intended for use with choked screens, where the
screen is significantly limiting the mass flow rate.
During the solution start-up phase, it may be necessary to specify a
low solidity, then increase it to the desired value to avoid
strong choking in transients.

*Keywords:* `SCREEN`

Heat exchangers may also be modeled at coupled zonal interfaces, using a
procedure similar to that used for actuator disks and screens.
The user specifies the zones and boundaries between which the heat
exchanger is located, the temperature increase across the heat
exchanger, and a static pressure loss coefficient.

*Keywords:* `HEAT-EXCHANGER`

Conjugate heat transfer is a term used to describe processes which
involve the thermal interaction between solids and fluids.
Wind-US includes the computational infrastructure needed for
coupling with the
*HTX*
solid conduction and convection heat transfer
code. A loosely-coupled approach is used whereby the routines pass
heat-transfer and temperature data, which become updated boundary
conditions for the modules.

*Keywords:* `TTSPEC`

Two models are available in Wind-US for including the effects of an array of vane-type vortex generators in three-dimensional flow. A vortex generator array consists of one or more vortex generators mounted on viscous wall boundaries.

The Wendt model
*[Dudek, J. C. (2006)
"An Empirical Model for Vane-Type Vortex Generators in a
Navier-Stokes Code,"
AIAA Journal,
Vol 44, No. 8, pp. 1779-1853;
Wendt, B. J. (2001)
"Initial Circulation and Peak Vorticity Behavior of Vortices Shed
from Airfoil Vortex Generators,"
NASA/CR-2001-211144]*
uses a discontinuous change in secondary velocity across a zonal
interface boundary in order to simulate the vortices produced by the
vortex generators.
The model determines the strength of each vortex based on the generator
chord length, height and angle of incidence with the incoming flow, as
well as the incoming flow core velocity and boundary layer thickness.

The BAY model
*[Bender, E. E., Anderson, B. H., and Yagle, P. J. (1999)
"Vortex Generator Modeling for Navier-Stokes Codes,"
FEDSSM99-69 19,
3rd Joint ASME/JSME Fluids Engineering Conference,
San Francisco, California]*.
is a source term model which models the side force produced by the
vortex generator and adds it to the momentum and energy equations.
This side force automatically adjusts its strength based on the local
flow.
The user specifies the grid points over which the force is to be
applied (i.e., enclosing each vortex generator).

*Keywords:* `VORTEX GENERATOR`

The effect of compressor/fan blade rows may be simulated in Wind-US
using an actuator duct model, originally developed at MIT.
*[Gong, Y.,
"A Computational Model for Rotating Stall and Inlet Distortion
in Multistage Compressors,"
Ph. D. Dissertation,
Dept. of Aeronautics and Astronautics,
Massachusetts Institute of Technology,
Cambridge, Massachusetts, 1999.]*
Unlike an actuator *disk* model, in which flow properties change
discontinuously across a computational plane, in the actuator *duct*
model the property changes occur within the finite computational region
containing the blade rows.
The effects of the blades on the flow are modeled by adding body force
source terms to the momentum and energy equations.

The user input needed to define the characteristics of the
turbomachinery being modeled is read from a set of
turbomachinery data files.
A separate file is required for each blade row, and currently each
blade row must be in a separate zone.
The names of the files, and the zone each file corresponds to, are
specified using the `TURBOSPEC`
keyword block.

The *x*-axis of the Cartesian coordinate system used in Wind-US
is assumed to coincide with the axial direction in the cylidrical
coordinate system used in the actuator duct model.
It's also assumed that the *i*, *j*, and *k*
computational indices correspond to the axial, radial, and
circumferential directions, respectively.
And, the zone extent must exactly match the blade; i.e., the leading
and trailing edges of the blade must lie in the upstream and downstream
zonal boundaries.

*Keywords:* `TURBOSPEC`

By default, Wind-US initializes the computational flowfield by setting
the flow properties at each grid point equal to those specified with
the `FREESTREAM`
keyword in the input data file.
The same initial conditions are applied at all points in the computational
domain, including solid walls, zone boundaries, and freestream boundaries.

Several options in Wind-US lead to non-default initializations, including user-specified inflow conditions, boundary layer initialization, and reinitialization of portions of the flowfield on restart. The user-specified inflow and boundary layer initialization options are currently only available for structured grids.

Wind-US's `ARBITRARY INFLOW`
keyword was designed to specify flow conditions at
`arbitrary inflow`
boundaries.
[Recall that the type of boundary, such as
`arbitrary inflow`,
is specified using
GMAN or
MADCAP,
and stored in the common grid (*.cgd*) file,
not in the input data file.]
However, it may also be used in a variety of ways to specify initial
conditions in selected portions of the computational domain that are
different from the freestream values.
This capability may be useful, for example, when modeling a jet
emanating from a solid wall.
Zones downstream of the jet exit may have difficulty converging
to the proper solution from conditions much different than the jet exit
conditions.

To use the `ARBITRARY INFLOW`
keyword as an initialization tool, specify the appropriate parameters and
values for a zone as described below, and run Wind-US from scratch
(i.e., without an existing flow (*.cfl*) file).
[Note that since the
`ARBITRARY INFLOW`
keyword is also used to specify boundary conditions at
`arbitrary inflow` boundaries,
a conflict arises if (for some reason) the desired inflow properties
are different from those being set as initial conditions.
In this case, the
`ARBITRARY INFLOW`
keyword can still be used to set initial conditions by setting the
number of cycles to be run to zero.
Then, after changing the values specified with the
`ARBITRARY INFLOW`
keyword to the desired inflow values, simply restart using the
initialized flowfield in the newly-created *.cfl* file.]

There are three ways that the
`ARBITRARY INFLOW`
keyword block may be used to modify the default initial conditions.

- If uniform inflow is specified for a particular zone using the
`UNIFORM`keyword, the flow*throughout that zone*will be initialized to the conditions specified.

- The
`IJK_RANGE`,`XYZ_RANGE`, and`RTZ_RANGE`keywords may be used to set flow conditions in specified regions. Up to 4000 total regions are allowed (for unstructured grids, surfaces specified using`USURFACE`are included in this number). The default initial conditions will be used at points outside the specified region(s).

- The
`USERSPEC`keyword may be used to specify a 1-D profile normal to the surface, translated through some buttline range, below the vehicle. Note that this option only applies to points in the*i*= 1 computational plane. The default initial conditions will be used at the remaining points.

To provide a better approximation to near-wall flowfields, Wind-US provides a couple of boundary layer initialization options that may help speed the convergence of viscous flows near solid walls.

First, by using multiple `IJK_RANGE` parameters with the
`ARBITRARY INFLOW` keyword,
and setting the range to include not only the inflow boundary
but also locations downstream, one can set initial boundary layer
profiles all along the viscous walls.
Note that using this capability may add many lines to the input data
(*.dat*) file.
The `INCLUDE` keyword may be
useful in keeping the main *.dat* file to a manageable size.

Another option is to use the
`BL_INIT` keyword to specify a
starting location and thickness for a laminar or turbulent boundary layer.
However, this option may only be used on computational *j*- or
*k*-boundaries, and only on one boundary in each zone.

*Keywords:*
`ARBITRARY INFLOW`,
`BL_INIT`

In the event that portions of the computed flowfield become "polluted" with unrealistic flowfield data, due to numerical instabilities or other causes, you may wish to reinitialize portions of the flow. Wind-US's reinitialization option enables you to reset the flow conditions in specified zones.

For both structured and unstructured grids, conditions throughout the
zone may be reinitialized to freestream values.
In addition, conditions within specified regions may be reinitialized to
values specified using the `ARBITRARY
INFLOW` keyword, and/or (for structured grids) the
`BL_INIT` keyword,
as described above.

*Keywords:*
`REINITIALIZE`,
`ARBITRARY INFLOW`,
`BL_INIT`