
number 
 Description



1  
Reserved for use at ITAC.

2   Designed for parallel processing data
transfer debugging.

mode  
Result 


1  
Don't read zonal boundary data (evrwbd)
 
2  
Not used
 
4  
Don't solve zone
(evsolv)
 
8  
Don't write zonal data
(evwzon)
 
16  
Don't write zonal boundary data
(evrwbd)
 
32  
Not used
 
64  
Not used
 
128  
Not used
 
256  
Don't update boundary conditions (structured grids only)
(lpschm)

Set mode equal to the sum of the desired actions.

3   Parallel processing
task tracing.

mode  
Action



1   Trace event reads/writes
(rwev)
 
2   Trace file I/O
(rwnh, rwc, rwd, rwi, rwr)
 
4   Trace network traffic
(psexit, psgscat, psrwev, psrwgv, psrwnh, psrwc,
psrwd, psrwi, psrwr, rwbc)
 
8   Trace task begin/end
(psspwn, tskbeg, tskidl)
 
16   Print task queue for debugging
(psqprt)

Set mode equal to the sum of the desired actions.
I.e., setting mode = 5 will trace both event reads/writes
and network traffic.

4  
Reserved for use at ITAC.

5   Flag for procedure
used in gas1 to compute effective specific heat ratio
β and sound speed a for frozen and finiterate
chemistry.

mode  
Procedure




> 0   Iterate on pressure,
with a maximum of mode iterations
 
< 0   Iterate on temperature,
with a maximum of 20 iterations

The default is to iterate on pressure, with a maximum of 20
iterations.
(gas1)

6   Write .cfl file compatible with the
"old" code.
(asnsx, asvisc)

7   Do not use high
performance C I/O interface.
(openf)

8   Use Version 2
common files.
(cftopn, mpinit, openf, zhinit)

9   For mode = 1,
run a verification case using the method of manufactured
solutions.
If mode = 2, in addition to running the case, Plot3d
function files named mms.exact.fxn, mms.cfd.fxn,
and mms.error.fxn are written containing the exact
solution, the WindUS solution, and the error.
The functional forms for the primitive variables are combinations
of sine and cosine functions, and are coded in subroutines
mms_3d_euler_bc and mms_3d_ns_bc for the Euler
and NavierStokes equations, respectively.
The corresponding source terms for the governing equations
are coded in subroutines mms_3d_euler_src and
mms_3d_ns_src.
The choice of an Euler or NavierStokes solution is determined by
the TURBULENCE keyword.
If the flow is inviscid in all zones, an Euler solution is
computed; otherwise, a constantviscosity laminar NavierStokes
solution is computed.
The flow may be 2D or 3D, as determined by the grid file.
Multizone grids may be used, but the use of
COUPLING MODE
CHARACTERISTIC is recommended for NavierStokes solutions.
(Viscous terms are neglected in Roe boundary coupling, and they
are large in the method of manufactured solutions.)
Frozen boundary conditions must
be specified in the grid file at all noncoupled boundaries.
The appropriate boundary conditions for the functional forms being
used will then be set automatically.
See Roach [Roach, P. J. (1998) Verification and Validation in
Computational Science and Engineering, Hermosa Publishers,
New Mexico], and Salari and Knupp [Salari, K. and Knupp,
P. (2000) "Code Verification by the Method of Manufactured
Solutions," SAND 20001444, Sandia National Laboratories,
Albuquerque, New Mexico], for more detailed information on the
method of manufactured solutions.
(l2norm1d, lpschm, mms_test_soln, nsrhss, pstinp, sins, tdbcni)

10   Print the time
step information (i.e., minimum/maximum CFL and Δt)
into the .lis file every mode cycles, instead of
just on the first cycle.
(NSzsolv)

11   Normally, the
flowfield is rotated to be consistent with changes in the global
angles of attack and sideslip.
This TEST option prevents that rotation.
(Changes in the global angles may occur at the start of a restart
run, if the user specifies angles that are different from the
values in the .cfl file, or during a run when the
FIXED_CL keyword is used.)
(lpgrp)

12   In the
HLLC scheme, use a more accurate
method for computing the wave speeds.
(hllc, US_HLLC, US_HLLCRL)

13  
Reserved for use at ITAC.

14   For structured
grids, write pressure to the .cfl file.
(It's always written for unstructured grids.)
(axflow)

15   For the SST model
with an ε limiter (the
LESB
keyword), modify the grid filter width Δ used in the limiter.
This test option only applies to structured grids.
(sst1, sst2, sst3)

mode  
Grid Filter Width



0  
max(ds_{1}, ds_{2},
ds_{3}, V dt,
k^{1/2} dt)
 
1  
max(ds_{1}, ds_{2},
ds_{3},
k^{1/2} dt)
 
2  
max(ds_{1}, ds_{2},
ds_{3}, V dt)
 
3  
max(ds_{1}, ds_{2},
ds_{3})

where ds_{1}, ds_{2}, and
ds_{3} are the distances along the grid lines in
the three directions, V is the velocity, k is the
turbulent kinetic energy, and dt is the time step size.

16   Manually set the
blowing Mach number for
BLOW
SURFACE boundary conditions to mode / 100.
The default is to compute the blowing Mach number from the local
flow conditions and the specified plenum conditions, with a
maximum value of 1.0.
(Note that this sets the actual blowing Mach number, not a
different maximum value.)
(BC_bcbled)

17   Use "new" BaldwinBarth turbulence model.
(bbarth)

18  
Use the integrated mass flux rather than a point by point mass flux
to determine the jump conditions of the
HEAT EXCHANGER model.
(BC_actud2, rwfghd, psrwgv)

19  
Allow the use of chemistry (.chm) files with
thermodynamic data in SPARKCRV or WINDNASA format,
even though those formats are now deprecated because they lack
information needed to correctly calculate entropy.
When using this option, total/static conversions are only
a rough approximation.
If possible, avoid this option and use chemistry files with
data in the NASA3287 format.

20  
Nondimensionalize k and ω
in the SST model the "old" way.
(aijkrg, aikeps, sstprtinp, sstpstprt)

21  
Flag affecting the initialization and freestream value of the
eddy viscosity for the SpalartAllmaras and Goldberg turbulence models.
(goldbergprtinp, goldbergpstprt, redimsa, sabound,
saprtinp, sapstprt, sinut, spalart, TURB_goldbergboundUS,
TURB_saboundUS)

mode  
Result



0, 1   Use
a default freestream value for
(ν_{t})_{∞} of
5.0, and initilize the dependent variable to
(ν_{t})_{∞} /
ν_{l}.
 
2   Use a default freestream
value for (ν_{t})_{∞}
of 0.1, and initilize the dependent variable to
(ν_{t})_{∞}.

In addition, for the SpalartAllmaras model in structured grids,

mode  
Result



0   Use the original 1992
model, with an f_{t2} term for
laminar stabilization.
 
1   Like mode 0, except with
"corrections" to the production and destruction terms.
This is equivalent to the default model for WIND beta
versions 4.15 to 4.92.
(Note that's "WIND," which predates "WindUS".)
 
2   Like mode 1, except
without the f_{t2} term.
This is equivalent to the default model for WIND versions
prior to WIND beta 4.15, and includes a slight error that
makes the model overly dissipative.


22   Compute the corrected
MASS FLOW RATE
based on areaaveraged total pressure and temperature rather than
areaaveraged static values.
(BC_pdsmfr)

25   In the BaldwinLomax model, use
y^{+} based on wall vorticity.
(blomax)

26   Use local values in y^{+}
damping for the BaldwinLomax, CebeciSmith, BaldwinBarth, and
kε models.
(bbdamp, blomax, cebeci, kepy2)

29   For the CebeciSmith
model, use y^{+} based on wall vorticity.
(algtur, cebeci)
For the kε models, TEST 29 is
a production limiter
(kelhssch, kelhssrg, keprod, kerhssch, kerhssrg,
redimkeps3d)

mode  
Result



0   Production limited to
20 × dissipation
 
1   Production computed from
vorticity, but not limited
 
2   Production not limited
 
3   Production computed from
vorticity, then limited
 
4   Production computed using
2μ_{t}S_{ij}S_{ij}, but not
limited
 
5   Production computed using
2μ_{t}S_{ij}S_{ij}, then
limited

Modes 4 and 5 only apply to the RumseyGatski ASM
kε model.

30   Irrotational boundary condition at
freestream inflow boundaries (structured zones only).
(BC_bcfree)

31   Use quadratic
curve fit when applying normal derivative boundary conditions
(∂p/∂n and ∂T/∂n)
at walls.
(BC_bcwall)

32   Modifies
the default handling of outflow boundaries.
This option is intended to improve performance when boundaries
in supersonic flow pass through an outflow boundary. For the
subsonic points, instead of imposing the downstream pressure
from the .dat file or using a simple extrapolation
(both of which have their problems), the TEST option
causes a search to be performed for the nearest supersonic
point, and the pressure at that point is used as the
downstream pressure.
(BC_preBC, US_tdbcg)

33   Hold the
temperature on a viscous wall at the current value, using the
conjugate heat transfer model.
See the
WALL TEMPERATURE FIXED
keyword for a similar capability.
(lpcycl)

34   Coefficient
for the streamwise vorticity term when using the BSL or SST
turbulence models with the net vorticity transport (NVT) option.
For details, see the description for
TEST 44.
(sstpk)

37   In wbnd2,
deallocate memory used for boundary coupling data before
returning.
(wbnd2)

38   Coefficient
for the streamwise velocity gradient term when using the BSL or SST
turbulence models with the net vorticity transport (NVT) option.
For details, see the description for
TEST 44.
(sstpk)

39   Used
with the BSL and SST turbulence models to specify freestream
sustainment terms.
(sstbound, sst2)

mode  
Result



0   Sustainment
terms are not used.
 
1   Sustainment
terms are used at all locations to preserve the
freestream turbulence values
(k,ω)_{∞}
set using the
FREE_K and
FREE_OMEGA
keywords.
 
>1   Sustainment
terms are used at all locations.
However two different levels of turbulence may be preserved.
In regions where
T_{t}<1.3*T_{t∞},
freestream turbulence values are sustained.
In regions where
T_{t}>1.5*T_{t∞},
(e.g., jet plumes)
engine turbulence values are sustained instead.
In intermediate regions, the sustainment terms
are linearly interpolated based upon the local
total temperature.
The engine turbulence values are computed by
treating mode as one thousand times the
intensity of turbulent kinetic energy relative
to the freestream velocity.
k = 1.5*(0.01*(mode/1000)*U_{∞})^{2}
ω = ω_{∞}
Thus, using mode 1000 would result in a
turbulence intensity of one percent.


*40*   Obsolete. Use
KE
COMPRESSIBILITY CORRECTION instead.
(keppstin)

41   Coefficient
for the density gradient term when using the BSL or SST
turbulence models with the net vorticity transport (NVT) option.
For details, see the description for
TEST 44.
(sstpk)

43   Specify
an alternate value for σ_{ω2},
the diffusion coefficient used in the ω transport equation
of the BSL and SST turbulence models.
(sstpstprt)

mode  
Result



0   Use the default value of 0.856.
 
n   Use a value of 0.001*n.


44   Controls
modifications of the turbulent kinetic energy production term,
\({\cal P}_k = \nu_T \Gamma^2\),
in the outer layer of the
BSL OR SST turbulence models.
These changes are referred to as Net Vorticity Transport (NVT)
modifications and are described by Bush (2014).
They are intended to incorporate sensitivity to thermal shear layers
by the inclusion of density gradient terms.
In order to understand what this option does, the following
definitions are needed:

Variable  
Description



\(\vec{\Omega} = \nabla \times \vec{V}\)  
Vorticity vector 

\(\Omega_s = \frac{\vec{V}}{\vec{V}} \cdot \vec{\Omega}\)  
Vorticity magnitude in streamwise direction.
if TEST(34)≠0, then multiply Ω_{s} by 0.001*TEST(34). 

\(\vec{D} = \frac{\nabla\rho}{\rho} \times \vec{V}\)  
Cross product of density gradient and velocity vector.
if TEST(41)≠0, then multiply D by 0.001*TEST(41). 

\(\Lambda\)  
A pseudostreamwise velocity gradient term (though not a proper vector quantity).
\(\Lambda = \vec{V} \cdot \left( \overrightarrow{ \frac{du}{dx}, \frac{dv}{dy}, \frac{dw}{dz} } \right)
\left/
\sqrt{\vec{V}^2 \cdot \left \left( \overrightarrow{ \frac{du}{dx}, \frac{dv}{dy}, \frac{dw}{dz} } \right) \right^2}
\right. \)
if TEST(38)≠0, then multiply Λ by 0.001*TEST(38). 
The resulting effect on turbulence production can then be described as:

mode  
Result



0   Use
the default \({\cal P}_k\) formulation,
based on vorticity:
\(\Gamma = \vec{\Omega}\).
 
1   Use
a modified \({\cal P}_k\) formulation,
based on the vector sum of \(\vec{\Omega}\) and \(\vec{D}\):
\(\Gamma = \vec{\Omega}+\vec{D}\).
Note that
\(\vec{\Omega}+\vec{D} = (1/\rho) \nabla \times (\rho\vec{V})\)
is related to the curl of momentum.
 
2   Use
a modified \({\cal P}_k\) formulation,
based on the turbulent stress tensor and momentum gradient:
\(\Gamma^2 = \frac{\tau_{ij}^{T}}{\rho\mu_T} \frac{\partial{\rho u_i}}{\partial{x_j}}\).
 
3   Use
a modified \({\cal P}_k\) formulation,
based on the amplitude sum of vorticity and density gradient
term:
\(\Gamma^2 = \vec{\Omega}^2 + \vec{D}^2\).
 
4   Reserved
for future use. Use
a modified \({\cal P}_k\) formulation,
based on the amplitude sum of vorticity and density gradient
term, and scaled by the streamwise velocity gradient term:
\(\Gamma^2 = (\vec{\Omega}^2 + \vec{D}^2)(1+\Lambda)\).
 
5   Reserved
for future use. Use
a modified \({\cal P}_k\) formulation,
based on the amplitude sum of vorticity and density gradient term,
less the streamwise vorticity,
and scaled by the streamwise velocity gradient term:
\(\Gamma^2 = ( \vec{\Omega}^2 + \vec{D}^2  \Omega_s^2)(1+\Lambda)\).
This value is forced to remain nonnegative.

Note that the above correction is only applied in the outer layer
of the model.
In the inner layer, the production term is computed from vorticity:
Γ=Ω. The same F1 blending function used to
switch model coefficients between inner and outer layer values is
used to switch between the inner and outer layer Γ values.
(sst2, sstpk)
[Bush, R.H. (2014)
"Turbulence Model Extension for Low Speed Thermal Shear Layers,"
AIAA Paper 20142086.]
See also:
TEST 34,
TEST 38,
TEST 41.

45   Activate
additional limiters recommended by Menter after the initial
development of the the BSL and SST
turbulence models.
(sst2)

mode  
Result



0   Extra limiters are not active.
 
1   Limit
the production of ω to be less than
20 times the dissipation of ω.
Also limit the magnitude of the crossdiffusion
term to 10 times the dissipation of ω
while maintaining the sign.


46   In the
BSL or SST turbulence models,
in blowing regions and
bleed regions with a specified
negative bleed flow rate, set
μ_{turb} = 10μ_{lam}
along the wall.
(sstbound, TURB_sstboundUS)

47   For the algebraic turbulence models,
smooth turbulent viscosity in each iplane using
simple averaging, with the number of smoothing passes set to
mode.
(smtvis)

48   For the algebraic turbulence models,
smooth turbulent viscosity in three dimensions using simple
averaging, with the number of smoothing passes set to
mode.
(smtvis)

49   Modified
smoothing for explicit operator for structured grids (see the
SMOOTHING keyword).
(bdload, dampi, dampj, dampk)

mode  
Result



2   No pressure switch on
secondorder dissipation, and ramp fourthorder
coefficient up and down
 
3   No pressure switch, and
an LES type filtering of nonlinear terms


*51*  
Obsolete. Replaced with the
MUT LIMITER
keyword option.
Original description was as follows:
Limit the turbulent viscosity μ_{T},
such that the maximum value of
μ_{T} / (μ_{L})_{∞} =
mode × 1000.
Suggested range is 50 < mode < 100.
Not valid with the kε models; use
KE
MAXIMUM TURBULENT VISCOSITY instead.
(keppstin, mutlim, TURB_mutlim, TURB_UpdateGoldberg,
TURB_UpdateSA, TURB_UpdateSST)

52   When using
BLOW PLENUM, print a
warning when the plenum total pressure is automatically raised
because it was less than the local static pressure.
(BC_bcbled)

54   Reserved for use at Boeing.

55   Reserved for use at Boeing.

56   No energy addition to fluid due to MFD
equations.
(emdef)

57   When an explicit
solution procedure is being used for the mean flow equations,
still solve the SpalartAllmaras and BSL/SST turbulence model
equations using an implicit method.
This test option only applies to structured grids.
(spalart, sst1, sst2, sst3)

58   For MFD flows, read the Lorentz force
directly from the .cfl file, but using the .cfl
file variable names normally used for the electric field.
Requires EFIELD CFL in the
MFD keyword block.
(emdef)

59   Apply
SMOOTHING keyword
values to the SpalartAllmaras model as well as the mean flow solver.
(Currently deactivated.)
(spalart)

60   Print warning when
local and coupled normal velocities have inconsistent directions at
a coupled boundary.
(postrbs)

61   When mode = 2,
all boundary conditions are applied, whether or not they're
consistent with the IBLANK values.
This only affects corners, where there are usually multiple
boundary conditions.
So, if a wall boundary at j = 1 meets an
outflow boundary at i = i_{max},
if TEST 61 2 is specified, both boundary
conditions are applied.
(tdbcgs)

62   Compute cell
areas and volumes using procedure from WIND 4.
This test option only applies to structured grids.
(mphzmet, nsrhsv, tdarea, vismet)

63   Eliminate the
"fat" boundary cells in any coordinate direction.
mode = 1, 2, or 4 indicates the i, j,
and k direction, respectively.
Set mode equal to the sum of the desired directions.
I.e., setting mode = 5 will eliminate the "fat"
boundary cells in the i and k directions.
This test option only applies to structured grids.
(mphzmet, nsrhsv, tdarea, tdarea2, vismet)

64   Remove dt from dq when
computing residuals.
(l2norm1d)

65   In marching solutions, lower the CFL
number for the last marching step.
(NSzsolv)

66   Don't update
β in gas3 for equilibrium chemistry.
This test option is not recommended but will decrease run time.
(gas3)

67   Flag affecting
boundary conditions for one and twoequation turbulence models
at bleed/blowing boundaries.
(kebc, sabound, sstbound, TURB_goldbergboundUS,
TURB_saboundUS, TURB_sstboundUS, vprtbound, vsctbound)

mode  
Result



0   Treat bleed/blowing
boundaries as noslip walls.
 
1   Treat bleed/blowing
boundaries as slip walls.
This was the default behavior prior to WIND 5.101.
 
2   Same as mode 0, except
do not use the procedure of Wilcox [Wilcox, D. C.,
Turbulence Modeling for CFD, DCW Industries, 2000]
to compute the boundary condition for omega in the
BSL or SST model.


68   If the density
is zero at a coupled boundary, issue a warning, ignore the
coupling data, and continue.
The default is to issue an error message and abort.
This test option only applies to structured grids.
(postrbs)

69   Rescale
the numerical roundoff in species mass fractions.

mode  
Result



0   (Default)
Multispecies cases with frozen or finiterate chemistry
solve ns − 1 species equations, where
ns is the number of species, and the mole fraction
for species number ns is set so that the total adds
to one.
All the numerical error is thus concentrated in the value
of the mole fraction for the last species.
 
1   A "dummy" last species
is used, whose mole fraction is always zero.
The Fortran variable ns is thus one more than the
actual number of species in the flow.
The code still solves ns − 1 equations, but
that now corresponds to all of the "real" species of interest.
In general the total of the mole fractions will not be exactly
1.0, so all the values are rescaled by a constant factor to make
it 1.0, spreading any numerical error over all the species.
The dummy species is not added automatically.
Thus, when this test option is used, the chemistry data
(.chm) file must be modified to add entries at the end
of the appropriate sections (i.e., thermodynamic coefficients,
finiterate coefficients, and transport properties) for the
dummy species.
The name of the dummy species doesn't matter, so one method would
be to simply copy the entry for one of the other species, and
change the species name to DUM to avoid confusion.
 
2   Similar to mode 1,
except that the dummy species is automatically created such that
the user need not modify the chemistry (.chm) file.

(bcrcpl, bqlinit, chprtinp, chpstin1, dbstate, dqlim1, dqlim2,
fixer, flagtbad, frtin1, gas1, gas1RL, gas2, gas3, gas4, gas4RL,
propin, qlr2bql, rates2a, ratesaa, ratesadla, ratesarr, ratesbea
ratesfa, ratesga, rhohcb, stomp, tdespair, transp, updatq1d,
updatqnp, US_Qcell2Qvrtx)

70   For mode
> 0, the tolerance level for converging gas properties
P, ρ, or T in gas2 will be set
to 10^{−mode}.
The default is 10^{−4}.
This only affects cases using TEST
99.
(gas2)

71   Calculation of
thermodynamic and
transport properties
from curve fit equations in .chm file.
(aichem, aijkrg, aikeps, airgun, aixyzrg, BC_bcfreebc,
BC_bcfreechar, BC_ijkfreechar, BC_usrffreechar, chpstin1,
chrhsv, cpfun, gas5, genturb, gibfn, hfun, kwinflow,
Part_Evap, pevap, phinit, pstinp, sfun, tdutv1, therm1,
trans1, transp, turbupd, uspeci)
For the thermodynamic properties,

mode  
Result



0  
Abort if the temperature exceeds the maximum for the curve
fits.
 
1  
Extrapolate if the temperature exceeds the maximum for
the curve fits, and write a warning message to the
.lis file.
 
2  
Same as mode 1, except without a warning message.
 
3  
If the temperature is outside the range of the curve fits,
use the values at the nearest limit.
 
4  
Use constant values consistent with a gas constant of
287 m^{2}/sec^{2}K, and a specific heat
at constant pressure of 1004.5 m^{2}/sec^{2}K.
 
5  
If the temperature is outside the range of the curve
fits, set the specific heat to its value at the nearest
limit and extrapolate for remaining properties.

For the transport properties, the meaning depends on which
formula (i.e., Sutherland's law or the NASA formula) is being
used, and whether the temperature is above or below the range of
the curve fits.

mode  
Result



0  
For most cases, abort if the temperature is outside the
range of the curve fits.
The only exception is for Sutherland's law with a
temperature lower than the minimum temperature for the
curve fits.
In that case, the values are extrapolated.
 
1  
For Sutherland's law, extrapolate if the temperature is
outside the range of the curve fits.
If the temperature is too high, a warning message is
written to the .lis file.
For the NASA formula, if the temperature is below the
minimum value T_{min}, apply Sutherland's
law with constants computed using the NASA formula at
T_{min}.
If the temperature is above the maximum value,
extrapolate.
A warning message is written to the .lis file in
both cases.
 
2, 4, 5  
Same as mode 1, except without a warning message.
 
3  
If the temperature is outside the range of the curve fits,
use the values at the nearest limit.


72, 73   For
structured grids, periodic boundaries may be established
by setting up double (or larger) fringes at the boundaries
using GMAN, with the boundary condition type specified as
frozen.
TEST options 72 and 73 provide the additional information
needed to apply the boundary condition.
TEST option 72 specifies the direction(s) of
periodicity, where values of 1, 2, and 4 indicate the i,
j, and k direction, respectively.
Set mode equal to the sum of the desired directions.
E.g., setting mode = 5 means periodicity in both
the i and k directions.
TEST option 73 specifies the depth of the fringes.
As an example, with TEST 72 1 (periodicity in the
i direction) and TEST 73 2 (a double fringe), we
have

Conditions at  
Come from



I = 1   I = IDIM  3
 
I = 2   I = IDIM  2
 
I = IDIM  1   I = 3
 
I = IDIM   I = 4

This procedure may only be used for periodic boundaries within a
single structured zone, with pointmatched grids in the source
and target regions.
It's primarily useful for cases with higherorder differencing
schemes, since the order of the scheme is preserved across
the boundary.
(kebc, sabound, sstbound, tdbcni, vprtbound, vsctbound)

74   Include
kdirection spacing when computing minimum time step in
2D or axisymmetric flows.
(tdtmst, tdvis1)

75   Stop with an
error message upon detecting an "Undefined" boundary
condition on any structured grid point. Unstructured grids always
perform this type of check by default.
(tdbcg)

76   Use
air C_{p} for implicit chemistry terms.
(rcutv1)

84   Use the "old" viscous metric calculation,
which averages the metric terms.
(emdsolv, vismet)

85   Check for zero volumes when computing
viscous metrics.
(emdsolv, vismet)

mode  
Result



1   Check; if ≤ 0 print
message and continue
 
2   Check; if ≤ 0 print
message and stop


87   Freezes supersonic inflow at initial
conditions.
(BC_bcfreechar)

88   Bypass checks
for negative density and pressure check in tdgas.
This is needed for chemically reacting flows if the heat of
formation varies widely, since we only have the old heat of
formation to use to estimate the temperature.
(ChangeGridsLin, lpschm, tdgas)

*89*  
Obsolete.
Original description was as follows:
Use "old" species flux correction method for multispecies flows.
(gas1, transp)

90   Chemistry stuff.
(chinv)

mode  
Result



0   Analytic chemistry Jacobian
(ns = 5 only)
 
1   Householder chemistry
Jacobian
 
2   Solves chemistry source term
explicitly


91   Gas constant.
(BC_bcfreebc, chpstin1, therm1)

mode  
Result



1   β =
γ = β_{∞}
 
2   β =
γ = 1.4


92   Utilize operator
splitting for the reacting chemistry source terms to increase the
stability of the integration, allowing more efficient solution of
the coupled system.
A 4thorder Pade approximation is used to integrate the reaction
source terms.
(chimplicit, chinv, chptimp, chrhss, US_chemsrc, US_chimplicit,
US_GaussSeidel)

mode  
Result



0   No operator splitting.
 
<0   Use operator splitting
and perform pointimplicit integration of the approximate
chemistry source terms where the number of subiterations
is mode.
For unstructured grids, pointimplicit is unavailable and
this option will be treated the same as mode>0.
 
>0   Use operator splitting
and perform implicit integration of the approximate
chemistry source terms where the number of subiterations
is mode.


*93*   Obsolete.
Replaced with the DIFFUSION NONE option in the
CHEMISTRY keyword
block.
(chrhsv, prtinp, rhsvfl, tdutv1, testprtinp)

94   Turn off implicit
chemistry terms.
This test option only applies to structured grids.
(tdimafk, tdimfu, tdimja, tdutaa)

95   Turn off
chemistry source term.
(rates, rates2, rates2a, ratesa, ratesaa, ratesadl,
ratesadla, ratesarr, ratesbe, ratesbea, ratesf, ratesfa,
ratesg, ratesga)

96   Gradually apply
chemistry source term over the first mode iterations for
finiterate chemistry.
(US_chemsrc, chrhss)

97   P. D. Thomas turbulence model scanning direction.
By default, WindUS starts at viscous walls and moves into the field.
This test option forces the code to calculate turbulent parameters
from any boundary, in addition to walls.
(algtur)

mode  
Result



0   use j lines
 
1   use k lines
 
2   use j and k lines


99   Initialize
finiterate chemistry with Liu and Vinokur curve fits.
(Also see TEST 70.)
(gas2)

mode  
Result



0   Do not track the species
(valid to 50K?)
 
1   Track the species
(valid to 10K?)


100   Timeaccurate
characteristic extrapolation for coupled, freestream, and inflow
boundaries.
(BC_bcfree, BC_test100)

mode  
Result



0   2ndorder, with
limit of ΔQ ≤ Q/2
 
1   1storder, original
characteristic treatment
 
2   2ndorder, original
characteristic treatment (only available for structured
grids)
 
3   1storder, Roe's average
characteristic treatment
 
4   2ndorder, Roe's average
characteristic treatment (only available for structured
grids)


102   Use
timeaveraged back pressure when applying specified mass flow
boundary condition at outflow boundaries.
(BC_pdsmfr)

104   Treatment of
implicit viscous terms.
This test option only applies to structured grids.
(rcutv1, tdutv1)

mode  
Result



0   Use simple implicit
viscous terms.
 
1   Turn off implicit
viscous terms.
 
2   Use fullyimplicit
viscous terms.
This only applies to the energy diffusion term for frozen
and finiterate chemistry.


105   Time step type.
This test option only applies to structured grids.
(iterprtinp, tdtmst)

mode  
Time Step Type



0   Δt =
CFL / max (λ_{ξ},
λ_{η},
λ_{ζ})
 
1   Flow angle scaling,
Δt = CFL ×
(f_{ξ} Δξ +
f_{η} Δη +
f_{ζ} Δζ), where
f_{ξ} =
[1 + tan θ + tan ψ]^{1/2}
f_{η} =
f_{ξ} tan θ
f_{ζ} =
f_{ξ} tan ψ
 
2   Velocity scaling,
Δt = CFL ×
min (f_{ξ} Δξ,
f_{η} Δη,
f_{ζ} Δζ), where
f_{ξ} =
u / u_{ξ} /
u_{ξ} + c
f_{η} =
u / u_{η} /
u_{η} + c
f_{ζ} =
u / u_{ζ} /
u_{ζ} + c
 
3   Δt =
CFL × min (Δξ, Δη,
Δζ) / (u + c)
 
4   Δt =
CFL / (λ_{ξ} +
λ_{η} +
λ_{ζ})


106   Compute
the time step at the start of every cycle (even when Newton
time stepping is being used), instead of at the start of every
iteration.
This test option only applies to structured grids.
(axflow, lpgrp, lpns, redim)

*107*  
Obsolete. Replaced with the
TEMPORAL SUBITERATIONS MODE {NEWTONDUALDT}
keyword option.
Original description was as follows:
Flag for choice of Newton and/or secondorder time algorithm;
0 to use the NPARC Alliance algorithm,
1 to use the Boeing algorithm.
This test option only applies to structured grids.
(bbarth, kestep, pstinp, rcimsc, spalart, sst, sst2, sst3,
tdimfu, tdimja, tdimsc)

108   Extrapolate
freestream outflow.
(This only applies to the old GMAN "freestream outflow" boundary
type, which is no longer used.)
(BC_bcfree, BC_bcfreebc)

mode  
Mach  
Outflow Conditions



0   < 1   Hold
upstream running characteristic at freestream
 
  > 1   Extrapolate
all, even in boundary layer
 
1   All   Extrapolate
all, even in boundary layer


109   Boundary flux treatment.
This test option only applies to structured grids.
(roewal, tdup1)
For tdup1:

mode  
Result



0   Conservative
 
1   Upwind extrapolation from
interior

For roewal:

mode  
Result



0   Characteristic inflow,
conservation if flow parallel to wall
 
1   Characteristic regardless
 
1000   Use conservative wall
treatment at all boundaries


110   Grid area
variation limiting.
This test option only applies to structured grids, and may
not be used with thirdorder fully upwind, fourthorder,
or fifthorder explicit operators, specified using the
RHS keyword.
(roecof)

mode  
A_{2} / A_{1}



0   ∞
 
1   2.0
 
2   1.5
 
3   1.33
 
4   1.1


111   Singular
matrix check.
This test option only applies to structured grids.
(jacpr4, jacpr5, jacprg, jacprg4, tdsol4, tdsol9, tdsol11,
tdsolg, tdsolg4, tdsolv)

mode  
Result



0   Check; if singular,
arbitrarily set diagonal term to 0.1, print a warning,
and continue.
 
1   Same as mode 0, but
without printing a warning.
 
2   Don't check.


112   Corrected upwind scheme at boundaries.
Defaults to corrected scheme, mode > 0 uses secondorder
smoothing with mode / 1000 as the smoothing level.
This test option only applies to structured grids.
Users should not use this option.
(rhsupw)

113   Check for
reverse flow at inflow and outflow boundaries.
(BC_bcconf, BC_bcfree)

mode  
Result



0, 1   Print a warning
message and continue.
 
2   Print an error message
and stop.
 
3   Set velocity to zero
and continue, with no warning message.
This mode only applies at
outflow boundaries.
 
4   Force a small outflow
velocity on
outflow boundaries
to prevent reversed flow at the exit.
 
5   Adjust the exit
pressure based on exit total pressure in order to
minimize inflow at
outflow boundaries.


114   Use central
differencing in the ζ direction when the Coakley explicit
operator is being used, with a central smoothing coefficient of
mode / 1000.
(tdup1)

115   Do not rescale inviscid wall total
velocity to equal adjacent value, just subtract the normal
component from the adjacent value.
(BC_bcvel, US_lhswall)

116   Set inward pointing normal to zero in
tdbcm1 at unknown grid topology points.
This test option only applies to structured grids.
(tdbcm1)

117  
Freeze conditions at inflow boundaries, even in subsonic flow.
(BC_bcfreebc, BC_tst100bc)

mode  
Result



1   Freeze all inflow.
 
2   Freeze only arbitrary
inflow points.
 
3   Freeze characteristics on
all i = 1 boundaries.
This mode value only applies to structured grids.


118   Singular axis
fix.
This test option only applies to structured grids.
(radavg)

mode  
Result



0   Average density, momentum
components, and pressure
 
1   Average density, velocity
components, and pressure


121   Underrelaxation
of points adjacent to singular axis.
This test option only applies to structured grids.
(bcpinw, bcsing, kebc, relsng, sabound, sngthrm,
sstbound, vprtbound, vsctbound)

mode  
Result



0   Value on axis is a
radiusweighted average of the values at the adjacent
points; values at the adjacent points are unchanged
 
n   Value on axis
computed as for mode 0; values at the adjacent points are
computed from
F_{adj} =
(1 − r) F_{adj} +
r F_{axis}
where F_{adj} is the value at the adjacent
point, F_{axis} is the axis value, and
r = n / 1000.


122   Allow lefthanded coordinates.
(tdarea1, tdarea2)

123   Track back
pressure, mass flow, and integrated total pressure for outflow
boundary conditions, writing the values into the .lis
file.
The back pressure will be in psi, and the integrated total
pressure will be the ratio of the boundary value to the
freestream value.
When the MASS FLOW
keyword is used, the mass flow value will actually be the ratio
of the computed value to the desired value.
For the other outflow boundary conditions the dimensional mass
flow is written, in lb_{m}/sec.
Note that when the
MASS FLOW keyword
is used, the back pressure and the mass flow are automatically
written into the .lis file, whether this test option is
used or not.
Specifying TEST 123 will add the integrated total
pressure.
Also note that when the
MASS FLOW keyword
is used, all three values may be extracted from the .lis
file using the resplt
(or resplt.pl)
utility.
For the other outflow boundary conditions, only the integrated
total pressure can be extracted.
(BC_IntgrtBnd, BC_pdsmfr)

124   Write the
accumulated time to the list output (.lis) file every
iteration instead of every cycle.
This test option only applies to singlezone structured grids,
with a CFL number specified using the
CFL# keyword mode 1 or
2, and with the trailing "ityp" input value set to 1 to
indicate that a global time step should be used equal to the
minimum value in the zone.
(print_res)

126   Compressibility
correction to BaldwinLomax turbulence model.
(blomax)

mode  
Result



0   No compressibility
correction; κ = 0.0168.
 
1   Use κ = 0.0180,
as in CFL3D.


127   For the
maximum and L2 residuals written to the list output (.lis)
file with the *RES* line identifier, scale the values by
the maximum value over all time steps.
Note that this does not apply to the residuals written using the
RESIDUAL_OUTPUT
keyword.
(print_res)

128   Check the L2
norm of the residual for convergence instead of the maximum
residual.
(GRD_MeshDeform, l2norm1d)

131   Reset the time
step for j index values < mode equal to the time
step at j = mode.
I.e., (Δt)_{i,j,k} =
(Δt)_{i,mode,k} for
j < mode.
This is intended for use with boundary layers on
j = 1 walls, to set the time step in the
boundary layer to a (larger) "outer" value.
(tdtmst)

132   Renormalize, changing from total to
static values.
The normalizing values in the .cfl file (e.g., the
freestream values in the fpar array in the global header)
are unchanged.
(redim)

134  
Order of extrapolation from interior to boundary values used at
freestream, arbitrary inflow, and outflow boundaries, and at
coupled boundaries using characteristic coupling.
(BC_bcptcond)

mode  
Result



2   Firstorder.
 
0, 1   Secondorder, using
a minmod limiter.
This mode value only applies to structured grids.


135   Reset the time step using a weighting
function between the ordinary Euler CFL number and a new "viscous
CFL number", for convergence acceleration in viscous layers.
The viscous CFL number is set to mode / 1000.
Limited testing indicates that a value of mode = 50 is
stable and increases the time step near the wall by at least
an order of magnitude.
This test option only applies to structured grids.
(tdtmst)

136   Divergence
checking criteria and action.
Set mode = n_{1} + 10 n_{2},
where n_{1} and n_{2} are defined
below.
(lpgrp)

n_{1}  
Divergence Definition



1   Max residual > 1.0,
L2 norm increasing
 
2   Max residual > 5.0,
L2 norm increasing
 
3   Max residual > 10.0,
L2 norm increasing

and

n_{2}  
Action Taken When Diverging



1   Terminate iteration for
current cycle
 
2   Abort run
 
3   Reduce CFL number by 1/2 and
terminate iteration for current cycle


137   Butt line interpolation region for
USERSPEC;
smear USERSPEC conditions over
0.001 × butt line at minimum and maximum butt line.
(uspeci)

mode  
Result



0   No interpolation
 
n   n = 0.001 ×
butt line for interpolation


138   Treatment
options for boundary cells.
This test option only applies to structured grids.
(BC_bcwall, chrhsv, mphzmet, nsrhsv, tdarea, tdarea1,
tdarea2, PreWallBC, US_tdbcg, vismet)

mode  
Result



≤ 1   Use large cells
 
2   Use large cells,
central difference Jacobian
 
3   Throw out half cell at
boundaries
 
5   Solve
∂P/∂n equation at walls


139   Turn on
gridbased flux limiting for the Coakley explicit operator, using
the limiting turning angle specified with the
GRID LIMITER
keyword.
(tdup1)

140   Use firstorder differencing when
computing the
∂(u,v,w) / ∂ξ
term in the vorticity used in the turbulence models.
This test option only applies to structured grids.
(sst2, sst3, vortcy)

141   Use
secondorder differencing for normal derivatives when applying
wall boundary conditions (for explicit boundary conditions only).
(BC_bcvel, BC_bcwall, US_tdbcg)

mode  
Result



1   Secondorder
∂p/∂n, ∂T/∂n,
and ∂u_{tan}/∂n
 
2   Secondorder
∂p/∂n and
∂T/∂n, but not
∂u_{tan}/∂n


142   Override
the abort that occurs when requesting time history with
steadystate calculations.
(thpstinp)

145   Ensure
the noslip velocity constraint on heat exchanger actuator disc
boundaries is enforced.
(bqlup2)

150   Singular axis
on symmetry planes.
When symmetry plane test fails, zero this component of velocity.
This test option only applies to structured grids.
(bcsing)

mode  
Result



1   u = 0
 
2   v = 0
 
3   w = 0
 
4   do not zero any component
(use average)
 
5   v = w = 0
 
6   u = w = 0
 
7   u = v = 0


151 
 For a singular axis, the value on the axis is a radiusweighted
average of the values two points away from the axis, instead of the
values at the adjacent points;
values at the adjacent points are set to the average of the axis
value and the value two points away from the axis.
E.g., for a singular axis at j = 1, with the
k direction "circumferential", the value on the axis is a
radiusweighted average of the values at j = 3,
instead of at j = 2.
Then for each k, the value at j = 2 is
set to the average of the values at j = 1 and
j = 3.
This test option only applies to structured grids, and overrides
TEST 121.
(bcpinw, bcsing, kebc, kerot, radavg, relsng, sabound,
sngthrm, sstbound, vprtbound, vsctbound)

*153*  
Obsolete. Replaced with the
MASS FLOW FREQUENCY
keyword.
Original description was as follows:
Iteration frequency for updating pressure at outflow boundaries.
The default is 5 for all the
DOWNSTREAM
PRESSURE modes except VARIABLE and
UNSTEADY, where the default is 1.
The default is also 1 when outflow boundary conditions are
specified using the
MASS FLOW,
DOWNSTREAM MACH, or
COMPRESSOR FACE
keyword.
(BC_IntgrtBnd)

154   When computing values at "undefined"
boundary points, and no neighboring nonhole, nonfringe, points
are found, average over neighboring fringe points.
This test option only applies to structured grids.
(bcundef, kebc, sabound, sstbound, vprtbound, vsctbound)

155   For unstructured
grids, extrapolate at freestream characteristic boundaries.
(BC_bcfree)

157  
Options for USERSPEC
inflow.
(uspeci)

mode  
Result



1   Put USERSPEC
inflow at all points in the buttline range.
Do not check for above/below vehicle.
 
2   Same as mode 1, but also
ignore fuselage station check.


158   Write various unstructured grid info to
.lis file.
(opngrd)

160   Pressure
correction factor = mode / 1000 for
specified mass flow boundary
condition.
The default is a pressure correction factor of 1.
(BC_pdsmfr)

162   Boundary layer edge definition for the
CebeciSmith turbulence model.
(cebeci)

mode  
Result



0   1.0% change in
U_{total} between grid points
 
1   0.995 H_{t}
 
2   0.99 U_{total}
 
3   0.9999 U_{total}


163   Criteria for defining F_{max}
in BaldwinLomax model.

mode  
Result



> 0   Search
outward from wall; use first peak in F that
is followed by a fractional decrease in F of
mode / 1000.
 
< 0   Use
the max F value between the wall and the
 mode 'th grid point from the wall

The default is use the first peak in F that is followed by
a fractional decrease of 70% (i.e., mode = 700).
(blomax)

164   Iteration
interval for updating gas
properties and species for ireal = 2 (i.e.,
equilibrium air chemistry).
The default value is 1.
(tdgas)

165   Sets the
tolerance for the distance between grid points used to determine
a singular direction to 10^{mode/1000}.
The default is a tolerance of 10^{−8} (i.e.,
mode = −8000).
This test option applies to structured grids only.
(bcsing, direct)

168   In a marching solution with the algebraic
turbulence models, begin turbulent flow at streamwise station
mode.
(tdvis1)

170   NASA Ames time step formula.
(CFL increases as 1/(Δy)^{1/2} near the wall.
Thus, Δt decreases as (Δy)^{1/2},
not Δy as the default.)
C_{A} is a scalar coefficient on CFL; i.e.,
CFL_{wall} is proportional to C_{A}.
This test option only applies to structured grids, and has no
effect if TEST 105 mode 1,
2, or 3 is used.
(tdtmst)

mode  
C_{A}



1   0.01
 
n   0.001n


172   Turn off base
energy for ireal = 3 (i.e., frozen and finiterate
chemistry).
(aichem, aijkrg, aikeps, aixyzrg, BC_bcfreechar,
BC_ijkfreechar, BC_test100, BC_usrffreechar, dqlim1, gas1,
gas2, gas3, gas4, gas5, gasint, pstinp, redimchem, stomp,
tdimfp, tdroe4, tdroe5, US_EnsightGama, US_EnsightMach,
uspeci)

174   For the algebraic turbulence models,
update the turbulent viscosity every mode iterations.
The default is 1.
(tdvis1)

175   Boundary conditions at freestream radial
outer boundaries.
(BC_bcfree, BC_bcfreechar, tdbcgs)

mode  
Result



0   Compute characteristics
from freestream conditions
 
1   Compute characteristics
from conditions at i = 1
along boundary
 
2   Extrapolate without testing
at k boundaries; treat i and j
boundaries as in mode 1


177   Freeze the maximum residual at the value
for the first iteration.
This test option applies to structured grids only.
(lpgrp)

178   For
finiterate chemistry with multispecies blowing (i.e., using
BLOW SPECIES_FRACTIONS with
BLOW MASS or BLOW
VALVE), gradually introduce the species over the first
mode iterations.
(BC_bcbled)

179   When solidbody rotation is specified at
an arbitrary inflow boundary, modify the rotation radius to get a
linear swirl profile in r with the zero velocity point not
at the specified center of rotation.
mode = 1000 r_{0}, where
r_{0} is the radius (from the point
x_{c}, y_{c}, z_{c}
specified using the SOLIDBODY keyword in the
ARBITRARY INFLOW
keyword block) for zero velocity.
(rotat)

180   For an
actuator disk with free vortex modeling (i.e., the TURNING
VORTEX keyword in the
ACTUATOR keyword
block), set the radius of the solidbody rotation core to
mode / 1000 inches.
The default is to set a solidbody core radius such that the
pressure at r = 0 is p_{∞} / 10.
(rotat1)

182   For Roe zonal coupling, don't modify the
boundary states at interior face points for consistency with
boundary values.
This test option applies to structured grids only.
(tdbcgs)

185   Flag used when
restarting a parabolized marching solution for cases with
equilibrium chemistry.
(gasint)

mode  
Result



1   Reset all flow field
values at unknown planes, including thermodynamic
properties (β, Z, heat of formation,
and sound speed), equal to those at the plane upstream of
first unknown plane.
This should only be necessary when using the
RESTART
keyword and specifying a restart plane upstream of the
last completed plane.
 
2   Reset thermodynamic
properties at the last computed plane to the reference
conditions.


187   The factor for suppression of the
streamwise pressure gradient in a marching solution is set to
mode / 1000.
The default factor is 0.95 (i.e., mode = 950), and
mode values below 800 are not recommended.
When separation or strong adverse pressure gradients are causing
problems, values between 800 and 900 will really help.
(rhsmar, tdimfp)

188  
Controls how structuredgrid SA/BSL/SST turbulence model data
is passed across coupled zones.
If the flow passes through a zone boundary at an angle, the
applied boundary values for the turbulence transport variables
are usually modified using a weighted average of the adjacent
value. This test option provides alternative treatments at
the interface.
(sabound, sstbound)

mode  
Result



0   Passing
of turbulence variables across the boundary is
weighted by the fraction of boundarynormal velocity
to the total magnitude.
 
1   Passing
of turbulence variables across the boundary is
simply based on whether the flow is in/out of the domain.
 
2   Turbulence
variables on coupled boundaries remain frozen at
current values.


189   If
a firstorder upwind explicit operator modified for stretched
grids is used (e.g.,
RHS ROE FIRST PHYSICAL),
then TEST 189 1 must also be specified.
(numprtinp)

190   Outgoing wave Roe boundary treatment.
This test option applies to structured grids only.
(pstinp, roecof, roeht, tdbcgs)

mode  
Result



0, 1   Use normal Roe
boundary treatment (uses boundary point in formulation).
 
2   Lower the order by one (does
not use boundary point in formulation).
This option cannot be used with
TVD in the same
zone, or with a fourthorder central or fifthorder
upwindbiased explicit operator.
 
3   Use zerothorder
extrapolation.


192   Save metrics in a temporary file.
After the first cycle, metrics will be read rather than computed.
This eliminates the CPU resources required to recompute the
metrics each cycle, but adds significant I/O to the computation.
In the past, on at least some Cray systems, this reduced the CPU
time by approximately 40.8 microseconds / (nodecycle).
On the more common platforms, however, it is generally faster to
recompute the metrics rather than store them.
(lpcycl)

193   Do not stop if a singular line
is encountered normal to a wall.
This test option applies to structured grids only.
(bbdamp, blinit, kepy2)

194   Bypass singular viscous metric check.
This test option applies to structured grids only.
(emdsolv, mphzmet, vismet)

195   When using
BLOW SURFACE, print a
warning when the flowfield static pressure becomes larger than
the plenum total pressure, causing blowing to be turned off
at that point.
Note that this is a fiveline message written for each iteration
and each "closed" node, and could cause the .lis file to
become very large very quickly.
(BC_bcbled)

196   For overlapping grids, print an error
message if there are no interior points adjacent to a fringe
point.
This test option applies to structured grids only.
(BC_norot, srfpar, tdbcgs)

197   Roe selfcoupling mode.
This test option applies to structured grids only.
(pstinp)

mode  
Result



0   Once per iteration, using
bcself
 
1   Once per cycle, using
standard zone coupling


199   Singular axis
averaging; average from 1 to (max − 1),
not 1 to max.
This test option applies to structured grids only.
(bcsing, linzero, radavg, relsng, sngthrm)

200   Don't bomb for negative speed of sound in
tdroe3A.
This test option applies to structured grids only.
(tdroe3A)
