This Page Contains Reference Material for
Input Parameters for TURBO.

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Input Parameter Description for the Parallel TURBO Code

TURBO reads the input parameters in namelist form. The namelists are read from the following files.
input00 contains parameters for the overall setup to run a case.
Blade row specific parameters are specified in input0x, where x is the number of the blade row.
 

File Name	Namelists
input00	PARAMETERS SOLUTION_PARAMETERS INITIAL_CONDITION REFERENCE_CONDITIONS k-e_MODEL_PARAMETERS TIME_SHIFT_BC SLIDING_BC INLET_BC  EXIT_BC FLUTTER TIME_STEP OUTPUT INLET_PROFILE EXIT_PROFILE
input01	BLADE_ROW_PARAMETERS (for blade row 1)
input02	BLADE_ROW_PARAMETERS (for blade row 2)

Click on one of the above links to skip to a namelist list
 

num_blade_rows

TURBO Source-code Name	mbr
Description	number of blade rows
Type	Integer
Default	1	Maximum	maxmbr	Minimum	1

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debug

TURBO Source-code Name	debug
Description	turns debug flag on, which:  produces verbose output checks for negative pressure in input and at the beginning of every residual calculation
Type	Logical
Default	false	Maximum	true	Minimum	false

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gofast

TURBO Source-code Name	gofast
Description	turns gofast flag on, which:  Suppresses message-passing inside Gauss-Seidel loop. This option makes the code run faster on some machines  but also possibly degrades convergence.
Type	Logical
Default	true	Maximum	true	Minimum	false

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num_printouts

TURBO Source-code Name	nprt
Description	Number of printouts.  The number of iterations run is the product of  num_printouts and num_iter_per_printout.
Type	Integer
Default	1	Maximum	none	Minimum	1

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num_iter_per_printout

TURBO Source-code Name	ntc
Description	Number of iterations per printout.  The number of iterations run is the product of  num_printouts and num_iter_per_printout.
Type	Integer
Default	160	Maximum	none	Minimum	1

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jacobian_update

TURBO Source-code Name	ifreq
Description	Flux jacobian update frequency (number of iterations per update),  generally 1 for unsteady flows.
Type	Integer
Default	1	Maximum	none	Minimum	1

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resid_print

TURBO Source-code Name	iresi
Description	Residual printout frequency.
Type	Integer
Default	1	Maximum	none	Minimum	1

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max_num_subiter

TURBO Source-code Name	itend
Description	Maximum number of subiterations.
Type	Integer
Default	1	Maximum	none	Minimum	1

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min_residual

TURBO Source-code Name	rmax
Description	log10 of the minimum residual at which it is  acceptable to end the subiteration loop.
Type	real
Default	-1.2	Maximum	none	Minimum	none

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num_iter_zero_grad_bc

TURBO Source-code Name	nzpd
Description	Number of initial iterations during which zero  pressure gradient boundary conditions are applied.  Some solutions require that the characteristic variable boundary conditions be delayed; in such cases, zero gradient boundary conditions are used initially.
Type	Integer
Default	-1	Maximum	none	Minimum	-1

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num_iter_first_order

TURBO Source-code Name	nfod
Description	Number of initial iterations during which first  order accurate discretization is used.  Some solutions require that the higher order spatial discretization schemes be delayed. This parameter controls both temporal and spatial discretization.
Type	Integer
Default	1	Maximum	none	Minimum	-1

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num_iter_infreq_jacobian_update

TURBO Source-code Name	nffd
Description	Number of initial iterations during which the flux jacobians are updated infrequently.  Using this parameter may save some computer resources.
Type	Integer
Default	0	Maximum	none	Minimum	0

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num_iter_inviscid

TURBO Source-code Name	nvsd
Description	Number of initial iterations during which flow is computed as inviscid.
Type	Integer
Default	-1	Maximum	none	Minimum	-1

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num_iter_without_fluxfix

TURBO Source-code Name	nfxd
Description	Number of initial iterations for which flux fixing is not used.
Type	Integer
Default	-1	Maximum	none	Minimum	-1

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symmetry_factor

TURBO Source-code Name	ksym
Description	Number of times that the set of modeled blade passages in a given blade row must be replicated to cover the full annulus.  For single blade row cases, ksym can be a fractional number. For example, to compute two blade passages in a 37-blade rotor, ksym=18.5.  ksym cannot be a fractional number for multiple blade row cases.  This parameter is only needed when periodic boundary conditions are applied on the blade-to-blade surface. When phase-lag b.c. is used, it must be set to zero.
Type	Real
Default	0.0	Maximum	none	Minimum	0

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restart_flag

TURBO Source-code Name	istrt
Description	Not necessary and not recommended for most simulations. Use in accordance with the following guidelines: When it is desired to use a previous TURBO solution as the initial flow condition for the next TURBO simulation (initialize_solution=4), set restart_flag=0. This will instruct TURBO to re-initialize the flowfield based on the previous TURBO solution: the flowfield shall be re-normalized, the phase-lag history shall be cleared, and the iteration count shall re-seed to zero. When it is desired to use a previous TURBO solution as the initial flow condition for the next TURBO simulation without re-normalizing the flow-field or clearing the phase-lag history, one may specify a nonzero value for restart_flag; the iteration counter shall re-seed to this restart_flag value. This setting is useful when seeking to analyze a previously resolved TURBO flowfield subject to different boundary conditions: e.g., analyzing an existing flowfield's response to a change in back pressure. When it is desired to use a previous APNASA solution as the initial flow condition for the next TURBO simulation (initialize_solution=2), restart_flag need not be specified here, as TURBO will read the iteration count history from the APNASA data files. When it is desired to merely restart and continue from a previous TURBO solution, the restart_flag should be outright removed from the input00 file (or set to correctly match the true iteration count history of the existing TURBO solution).
Type	Integer
Default	0	Maximum	none	Minimum	0

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num_iter_restart_write

TURBO Source-code Name	ndcyc
Description	Number of iterations between writes of the restart file(s).
Type	Integer
Default	160	Maximum	none	Minimum	1

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slip_bc_type

TURBO Source-code Name	slip_bc_type
Description	Slip boundary condition type. 1:  Original 2:   Improved
Type	Integer
Default	1	Maximum	2	Minimum	1

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freeze_jacobian

TURBO Source-code Name	jbfreeze
Description	Turns the jacobian freeze logic on and off. 1:   freeze jacobians after they are computed on the first subiteration  0:   compute jacobians every subiteration
Type	Integer
Default	1	Maximum	1	Minimum	0

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num_sgs_iter

TURBO Source-code Name	isgs
Description	Number of Gauss-Seidel passes for each subiteration
Type	Integer
Default	2	Maximum	none	Minimum	1

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solution_type

TURBO Source-code Name	istype
Description	Solution type.  0:    inviscid  1:    laminar viscous  2:    turbulent viscous
Type	Integer
Default	2	Maximum	2	Minimum	0

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turbulence_model

TURBO Source-code Name	itbmdl
Description	Turbulence model selection (currently only the CMOTT k-e model is available).  5:   k-e model with Newton scheme
Type	Integer
Default	5	Maximum	5	Minimum	5

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temporal_accuracy

TURBO Source-code Name	theta & psi
Description	Sets temporal accuracy.  1:   first-order accurate  2:   second-order accurate
Type	Integer
Default	2	Maximum	2	Minimum	1

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spatial_accuracy

TURBO Source-code Name	order & phi
Description	Sets spatial accuracy.  1:  first-order  2:  second order  3:  third order
Type	Integer
Default	3	Maximum	3	Minimum	1

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limiter_flag

TURBO Source-code Name	limit
Description	Selects limiter.  1:  Minmod for use with second and third order spatial discretization  2:  Superbee for use with second order space only  3:  Van Leer for use with second order space only
Type	Integer
Default	1	Maximum	3	Minimum	1

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spatial_scheme

TURBO Source-code Name	muscl
Description	Flux scheme flag.  0:   hybrid flux extrapolation scheme  1:   MUSCL scheme; variable extrapolation
Type	Integer
Default	0	Maximum	1	Minimum	0

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wall_bc_limiter_flag

TURBO Source-code Name	limbc
Description	Limiter for wall fluxes. 0:   no limiter  1:   Van Leer
Type	Integer
Default	0	Maximum	1	Minimum	0

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wall_bc_first_order_i

TURBO Source-code Name	ifolyr
Description	Number of grid surfaces in the I-grid direction using first order spatial accuracy.
Type	Integer
Default	1	Maximum	none	Minimum	1

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wall_bc_first_order_j

TURBO Source-code Name	jfolyr
Description	Number of grid surfaces in the J-grid direction using first order spatial accuracy.
Type	Integer
Default	1	Maximum	none	Minimum	1

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wall_bc_first_order_k

TURBO Source-code Name	kfolyr
Description	Number of grid surfaces in the K-grid direction using first order spatial accuracy.
Type	Integer
Default	1	Maximum	none	Minimum	1

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trap_negative

TURBO Source-code Name	trap_negative
Description	Switch to abort program when negative pressure/density is found.  T:   program aborted if pressure/density at any cell is negative,        pressure_clip automatically set to 0.0  F:   program not aborted if pressure at any cell is less than the        value set by pressure_clip. Instead, correction of solution is        initiated.
Type	Logical
Default	F	Maximum	T	Minimum	F

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solution_correct_method

TURBO Source-code Name	solution_correct_method
Description	Method of correcting solution when pressure at any  cell is less than the value set by pressure_clip.  1:  pressure correction; same as APNASA correction.  2:  residual correction
Type	Integer
Default	1	Maximum	2	Minimum	1

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pressure_clip

TURBO Source-code Name	pressure_clip
Description	Solution corrected if pressure at any cell is less than this value.
Type	Real
Default	0.02*gamma	Maximum	1.	Minimum	0.0

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initialize_solution

TURBO Source-code Name	init_flw
Description	Selects initalization option.  (Note: files output from GUMBO are double-precision and right-handed)  1:   uniform flow  2:   read APNASA vstage-format file  3:   read APNASA HDF-format file, not available  4:   read TURBO restart, restart_flag must be set to 0
Type	Integer
Default	2	Maximum	4	Minimum	1

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freestream_mach_num

TURBO Source-code Name	fsmach
Description	Mach number used to initialize solution when initialize_solution=1.
Type	Real
Default	0.0	Maximum	none	Minimum	0.0

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tangential_angle

TURBO Source-code Name	t_ang
Description	Tangential flow angle:  With positive axial flow downstream, positive to turn flow CCW; negative to turn flow CW.  [Input in direct compliance with APNASA convention]
Units	Degree
Type	Real
Default	0.0	Maximum	none	Minimum	none

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radial_angle

TURBO Source-code Name	r_ang
Description	Radial flow angle: With positive axial flow downstream, postive to turn flow radially outward; negative to turn flow radially inward. [Input in direct compliance with APNASA  convention]
Units	Degree
Type	Real
Default	0.0	Maximum	none	Minimum	none

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thru_ic_flag

TURBO Source-code Name	thru_ic
Description	When enforced, initial flow condition is "through-flow", where primary flow is aligned with flowpath (local streamwise i-direction); if not enforced,  primary initial flow is directed axially parallel to centerline. This option is useful when analyzing radial/ centrifugal flows. Only applicable when restart_flag=0 and initialize_solution=1. 0:   Through-flow not enforced (Initial Flow parallel to centerline) 1:   Through-flow enforced (Initial Flow parallel to flowpath) The magnitude of the (non-dimensional) initial velocity vectors is equal  to the "fsmach" defined in input00 (just as for the uniform-flow case).
Units	None
Type	Integer (flag)
Default	0	Maximum	1	Minimum	0

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ref_pressure

TURBO Source-code Name	pref
Description	Reference pressure.
Units	Pa (=N/m**2)
Type	Real
Default	101325.	Maximum	none	Minimum	>0

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ref_temperature

TURBO Source-code Name	tref
Description	Reference temperature.
Units	K
Type	Real
Default	288.15	Maximum	none	Minimum	>0

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ref_velocity

TURBO Source-code Name	vref
Description	Reference velocity [equals sqrt(Rgas*Tref)].
Units	m/s
Type	Real
Default	287.6	Maximum	none	Minimum	>0

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ref_gamma

TURBO Source-code Name	gam
Description	Reference gamma; ratio of specific heat coefficients
Type	Real
Default	1.4	Maximum	1.667	Minimum	>1

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ref_length

TURBO Source-code Name	diam
Description	Reference length used to normalize the grid files.
Units	m
Type	Real
Default	1.0	Maximum	none	Minimum	>0

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gamma_table

TURBO Source-code Name	gam_table
Description	Gamma table for real gas calculations
Type	Real, dimension(2)
Default	1.4	Maximum	1.667	Minimum	>1

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temp_gam_table

TURBO Source-code Name	temp_gam
Description	Temperature table for real gas calculations.
Units	K
Type	Real, dimension(2)
Default	518.67,  618.67	Maximum	none	Minimum	>0

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gamref_t1

TURBO Source-code Name	gamref_t1
Description	Gamma to set ground internal energy; ener1.
Type	Real
Default	1.4	Maximum	1.667	Minimum	>1

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sutherland_const1

TURBO Source-code Name	suthc1
Description	First Sutherland's law constant.
Units	Pa*s
Type	Real
Default	see below	Maximum	none	Minimum	>0

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sutherland_const2

TURBO Source-code Name	suthc2
Description	Second Sutherland's law constant.
Units	K
Type	Real
Default	110.	Maximum	none	Minimum	>0

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_______________________________________________

k-e_MODEL_PARAMETERS namelist

Namelist Name	TURBO Source-code Name
kemdl_input_type  kemdl_init_option  inlet_turbulence_intensity inlet_eddy_viscosity  spatial_accuracy_2eq  temporal_accuracy_2eq  use_pgrad_term use_emut_wall_damping max_num_subiter_2eq  limiter_flag_2eq  jacobian_update_2eq num_sgs_iter_2eq cmu_clip_max dmut_clip_max	ke_input keinit tiint evtint order2 & phi2 theta2 & psi2 use_pgrad_term use_emut_wall_damping itend2 limit2 ifreq2 isgs2 cmumax dmut_clip_max

[back] Click on one of the above links to skip to a namelist

kemdl_input_type

TURBO Source-code Name	ke_input
Description	Legacy parameter no longer used.
Type	Integer
Default	1	Maximum	1	Minimum	0

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kemdl_init_option

TURBO Source-code Name	keinit
Description	k-e field initialization option.  0:  start from scratch  1:  start from APNASA initial flow  This parameter is ignored for restart runs.
Type	Integer
Default	1	Maximum	1	Minimum	0

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inlet_turbulence_intensity

TURBO Source-code Name	tiint
Description	Inlet turbulence intensity in fraction. Example: 0.01 for 1%.
Type	Real
Default	0.01	Maximum	1.00	Minimum	0.00

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inlet_eddy_viscosity

TURBO Source-code Name	evtint
Description	Inlet turbulent eddy viscosity ratio (relative to reference laminar viscosity).
Type	Real
Default	100.0	Maximum	none	Minimum	0.0

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spatial_accuracy_2eq

TURBO Source-code Name	order2 & phi2
Description	Spatial accuracy for the turbulent transport equations.
Type	Integer
Default	mean flow	Maximum	3	Minimum	1

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temporal_accuracy_2eq

TURBO Source-code Name	theta2 & psi2
Description	Temporal accuracy for the turbulent transport equations.
Type	Integer
Default	mean flow	Maximum	2	Minimum	1

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use_pgrad_term

TURBO Source-code Name	use_pgrad_term
Description	Includes streamwise pressure-gradient term in the wall function treatment.  T:  include Not recommended for compression system flows; use only for turbine flows. F:   not include
Type	Logical
Default	true	Maximum	true	Minimum	false

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use_emut_wall_damping

TURBO Source-code Name	use_emut_wall_damping
Description	Switch for near-wall eddy viscosity damping. Only effective when using wall-function modeling.  T:   on  F:   off
Type	Logical
Default	T	Maximum	true	Minimum	false

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max_num_subiter_2eq

TURBO Source-code Name	itend2
Description	Maximum number of subiterations for the resolution of the two turbulent transport equations.
Type	Integer
Default	1	Maximum	None	Minimum	1

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limiter_flag_2eq

TURBO Source-code Name	limit2
Description	limiter flag for the two turbulent transport equations.  0:   no limiter  1:   use limiter (Van Leer)
Type	Integer
Default	1	Maximum	1	Minimum	0

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jacobian_update_2eq

TURBO Source-code Name	ifreq2
Description	Flux jacobian update frequency (number of subiterations per update) for the resolution of the two turbulent transport equations.
Type	Integer
Default	1	Maximum	None	Minimum	1

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num_sgs_iter_2eq

TURBO Source-code Name	isgs2
Description	Number of symmetric Gauss-Seidel subiterations to be performed during resolution of the two turbulent transport equations.
Type	Integer
Default	1	Maximum	None	Minimum	1

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cmu_clip_max

TURBO Source-code Name	cmumax
Description	Upper limit of Cmu for standard K-e modeling.
Type	Real
Default	1	Maximum	None	Minimum	0.0

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dmut_clip_max

TURBO Source-code Name	dmut_clip_max
Description	Upper limit of eddy viscosity.
Type	Real
Default	1	Maximum	None	Minimum	0.0

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use_time_shift_bc

TURBO Source-code Name	iflagts
Description	Turns time shift boundary conditions on  0:  off  1:  on
Type	Integer
Default	1	Maximum	1	Minimum	0

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time_shift_bc_factor

TURBO Source-code Name	frlx
Description	Time shift boundary condition underrelaxation factor.
Type	Real
Default	0.75	Maximum	1.0	Minimum	0.

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initialize_time_shift_in_TURBO

TURBO Source-code Name	initialize_time_shift_in_TURBO
Description	Initialize time-shift history data in TURBO.
Type	Logical
Default	F	Maximum	T	Minimum	F

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use_conserve_bc

TURBO Source-code Name	iflagcon
Description	Use flux conservation b.c.  for sliding interface at blade_to_blade interface  0:  off  1:  on, use only for full-simulation. Not recommended for              phase-lag approximation.
Type	Integer
Default	0	Maximum	1	Minimum	0

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inlet_bc_type

TURBO Source-code Name	ibtype(1)
Description	sets inlet boundary condition type   1:   characteristic variable subsonic inflow         not recommended, use only in 2D cascade test         bc type=cvbc_in +2:   isentropic subsonic inflow, uniform total conditions held          bc type=isentropic_in -2:   isentropic subsonic inflow, radial profile of          total conditions held          bc type=isentropic_in  3:  1-D nonreflecting boundary condition, steady inlet base        flow read in from unit 31 (cor.inlet_steady)        bc type=wb_steady_in  4:   1-D nonreflecting boundary condition, unsteady inlet         base flow read in from unit 31 (cor.inlet_unsteady)         bc type=wb_unsteady_in 5:   2-D nonreflecting boundary condition Still in development and validation; currently not available.
Type	Integer
Default	3	Maximum	5	Minimum	-2

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num_blade_us

TURBO Source-code Name	nbld_us
Description	Number of blades in the upstream blade row. This parameter is only used for wake blade analyses
Type	Integer
Default	0	Maximum	none	Minimum	0

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omega_blade_us

TURBO Source-code Name	omega_us
Description	Wheel speed of the upstream blade row. This parameter is used only for wake blade analyses.
Units	RPM  APNASA convention; a left-handed system. Positive for CCW-rotating when looking downstream.
Type	Real
Default	0.	Maximum	none	Minimum	none

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num_tangential_cells_us

TURBO Source-code Name	mkus
Description	Number of cells in the tangential direction base flow file which describes the inlet disturbance. This parameter is used only for wake blade analyses.
Type	Integer
Default	num_grid_tangential (read from BLADE_ROW_PARAMETERS namelist for the first blade row or from the HDF grid file if initialize_solution=4)
Maximum	none	Minimum	>0

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exit_bc_type

TURBO Source-code Name	ibtype(2)
Description	sets exit boundary condition type  +1:   characteristic variable subsonic outflow with radial          equilibrium, pressure imposed at the hub          bc type=radial_eq_exit -1:   characteristic variable subsonic outflow with radial          equilibrium, pressure imposed at the casing          bc type=radial_eq_exit  2:   1-D nonreflecting BC, static base flow read from cor.exit_steady         bc type=wb_steady_exit  3:   1-D nonreflecting boundary condition, unsteady exit         flow read from cor.exit_unsteady         bc type=wb_unsteady_exit  4:   characteristic variable supersonic outflow         bc type=cvbc_super_exit  5:   characteristic variable subsonic outflow         bc type=cvbc_sub_exit  6:   2-D nonreflecting boundary condition Still in development and validation; currently not available All the following are of bc type=pressure_exit: 11:   hold static pressure profile  12:   hold average area-average static pressure profile  21:   hold exit physical mass flow, corrected by pressure  22:   hold exit corrected mass flow, corrected by pressure  23:   hold exit physical mass flow, corrected by density  24:   hold exit corrected mass flow, corrected by density
Type	Integer
Default	2	Maximum	24	Minimum	-1

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back_pressure

TURBO Source-code Name	backp
Description	static pressure at exit
Units	Pa (=N/m**2)
Type	Real
Default	0.0	Maximum	none	Minimum	0.0

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num_blade_ds

TURBO Source-code Name	nbld_ds
Description	Number of blades in the downstream blade row. This parameter is only used for potential/blade analyses.
Type	Integer
Default	0	Maximum	none	Minimum	0

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omega_blade_ds

TURBO Source-code Name	omega_ds
Description	Wheel speed of the downstream blade row.  This parameter is used only for potential/blade analyses.
Units	RPM  APNASA convention; a left-handed system.  Positive for CCW-rotating when looking downstream.
Type	Real
Default	0.0	Maximum	none	Minimum	none

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num_tangential_cells_ds

TURBO Source-code Name	mkds
Description	Number of cells in the tangential direction base flow file which describes the exit disturbance. This parameter is used only for potential/blade analyses.
Type	Integer
Default	num_grid_tangential (read from BLADE_ROW_PARAMETERS namelist for the last blade row or from the HDF grid file if initialize_solution=4)
Maximum	none	Minimum	>0

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flutter_grid_type

TURBO Source-code Name	iflag_bv
Description	turns on the capability to use a different grid for each time step        0:   no flutter simulation, the same grid for all time steps        1:   read a new grid for each time step        2:   compute a new grid for each time step              from real and imaginary grid perturbations              specified in the displacement file.              Data in cylindrical coordinates.      -2:  same as 2.              Data in Cartesian coordinates.
Type	Integer
Default	0	Maximum	2	Minimum	-2

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flutter_freq

TURBO Source-code Name	omega_bv
Description	flutter frequency of the blade
Units	Hertz
Type	Real
Default	0.	Maximum	none	Minimum	0.

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flutter_phase_angle

TURBO Source-code Name	phi_bv
Description	Interblade phase angle
Units	Degrees
Type	Real
Default	0.	Maximum	360.0	Minimum	0.0

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cfl

TURBO Source-code Name	cfl
Description	CFL number  Based on the value of the CFL number, there are two ways to define the marching time step:  CFL /= 0. time step is determined by the definition of CFL number.  CFL = 0., time step is determined by the wheel speed.
Type	Real
Default	0.0	Maximum	none	Minimum	0.0

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use_local_time_step

TURBO Source-code Name	local
Description	Turns on the capability to use local time stepping  0:   same time step for all cells  1:   use constant CFL to set time step
Type	Integer
Default	0	Maximum	1	Minimum	0

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The following three parameters are used when CFL=0

num_time_steps_per_period

TURBO Source-code Name	ntm_stp
Description	Number of time_steps required to rotate through one blade passage (with num_blds_ts passages comprising a full annulus) at a rotational speed of omega_ts.
Type	Integer
Default	160	Maximum	none	Minimum	1

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omega_ts

TURBO Source-code Name	omega
Description	Wheel speed used to compute the time step size when CFL=0.
Units	RPM
Type	Real
Default	Default is case dependent:  For multiple blade row solutions:  relative wheel speed between first and second blade row  For wake/blade analyses:  relative wheel speed between inlet BC and blade row 1  For potential/blade analyses:  relative wheel speed between exit BC and blade row 1
Maximum	none	Minimum	none

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num_blds_ts

TURBO Source-code Name	nb1row
Description	Blade count used to compute the time step size when CFL=0
Type	Integer
Default	Default is case dependent:  For multiple blade row solutions: blade count of second blade row  For wake/blade analyses: blade count of the inlet BC  For potential/blade analyses: blade count of the exit BC
Maximum	none	Minimum	>0

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output_format

TURBO Source-code Name	iout
Description	selects output format  1:  NASA VSTAGE format  2:  Cell-Center format  3:  PLOT3D format  4:   HDF 5:  Time series in PLOT3D
Type	Integer
Default	4	Maximum	5	Minimum	1

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num_iter_per_soln_dump

TURBO Source-code Name	np3d
Description	Number of time steps between dumps of a solution
Type	Integer
Default	4	Maximum	none	Minimum	1

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num_soln_per_flow_file

TURBO Source-code Name	num_soln_per_flow_file
Description	Number of solutions in a flow file.  Flow files created automatically with name ast.b#1.q.#2, where #1 is the block (processor) number and #2 is the iteration number at which the file is created.
Type	Integer
Default	1	Maximum	none	Minimum	1

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num_parallel_writes

TURBO Source-code Name	num_parallel_writes
Description	Number of processors that write output (restart or plot) files at any particular time. This parameter allows sequential writes of output files to avoid data bus jam but increases waiting time.
Type	Integer
Default	9999	Maximum	none	Minimum	1

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itime_start_anim

TURBO Source-code Name	itanim
Description	When time shift simulations reach a periodic state,a time series of solutions is needed for flow visualization or animation. This parameter sets the starting time step for solution output. The ending step is determined automatically.
Type	Integer
Default	99999	Maximum	none	Minimum	1

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tmavg_output

TURBO Source-code Name	tmavg_output
Description	If checked,  time-averaged solution covering a single run will be generated in addition to the regular output.
Type	Logical
Default	F	Maximum	T	Minimum	F

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span

TURBO Source-code Name	none
Description	fraction of span for inlet boundary condition
Units	non-dimnesional
Type	Real
Default		Maximum	1	Minimum	0

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total_pressure

TURBO Source-code Name	none
Description	total pressure profile at the inlet
Units	Pascal (=N/m**2)
Type	Real
Default	pref	Maximum	none	Minimum	0

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total_temperature

TURBO Source-code Name	none
Description	total temperature profile at the inlet
Units	deg. K
Type	Real
Default	tref	Maximum	none	Minimum	0

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tangential_angle

TURBO Source-code Name	none
Description	Tangential flow angle at the inlet :  With positive axial flow downstream, positive to turn flow CCW; negative to turn flow CW.  [Input in direct compliance with APNASA convention]
Units	degrees
Type	Real
Default	0	Maximum	90	Minimum	-90

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radial_angle

TURBO Source-code Name	none
Description	Radial flow angle at the inlet: With positive axial flow downstream, positive to turn flow radially outward; negative to turn flow radially inward.  [Input in direct compliance with APNASA convention]
Units	degrees
Type	Real
Default	0	Maximum	90	Minimum	-90

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span

TURBO Source-code Name	none
Description	fraction of span for exit boundary condition
Units	non-dimnesional
Type	Real
Default		Maximum	1	Minimum	0

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static_pressure

TURBO Source-code Name	none
Description	static pressure profile at the exit (used for exit bc's 11 & 12)
Units	Pascal (=N/m**2)
Type	Real
Default	pref	Maximum	none	Minimum	0

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exit_mass_flow

TURBO Source-code Name	none
Description	exit mass flow rate to hold (used for exit bc 23)
Units	kg/s
Type	Real
Default	0	Maximum	none	Minimum	0

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num_blades

TURBO Source-code Name	nbld
Description	number of blades for this blade row
Type	Integer
Default	1	Maximum	none	Minimum	1

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omega_bld

TURBO Source-code Name	dtdt
Description	wheel speed of this blade row
Units	RPM  APNASA convention; a left-handed system.  Positive for counter-clockwise rotation when looking downstream.
Type	Real
Default	0	Maximum	none	Minimum	none

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num_time_steps_stored

TURBO Source-code Name	mlast
Description	number of time steps stored in phase lag boundary conditions storage  Note: if phase-lag b.c. is not used, this parameter must be -1
Type	Integer
Default	61	Maximum	none	Minimum	1

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num_adjacent_blades

TURBO Source-code Name	mgcd
Description	For two blade row simulations: number of blades in adjacent blade row which is used to compute periodicity of the disturbances coming from the adjacent row  For more than two blade row simulations: the greatest common divider of the number of blades of  the two adjacent blade rows  For flutter simulations: set by the code based on the interblade phase shift
Type	Integer
Default	Default is case dependent:  For multiple blade row solutions:  blade row 1: number of blade in blade row 2  blade row 2-mbr: number of blades in the previous blade row  For wake/blade analyses: blade count of the inlet BC  For potential/blade analyses: blade count of the exit BC
Maximum	none	Minimum	>0

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suction_surface

TURBO Source-code Name	isuct
Description	flag for which side of the blade is the suction surface  1:   k=1 surface is the suction side  2:   k=num_grid_tangential surface is the suction surface
Type	Integer
Default	1	Maximum	2	Minimum	1

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use_wall_func_i

TURBO Source-code Name	nwfci
Description	wall function flag for i direction  0:  off  1:   on
Type	Integer
Default	1	Maximum	1	Minimum	0

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use_wall_func_j

TURBO Source-code Name	nwfcj
Description	wall function flag for j direction  0:   off  1:   on
Type	Integer
Default	1	Maximum	1	Minimum	0

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use_wall_func_k

TURBO Source-code Name	nwfck
Description	wall function flag for k direction  0:  off  1:  on
Type	Integer
Default	1	Maximum	1	Minimum	0

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num_sources

TURBO Source-code Name	msr
Description	Number of sources in a blade row. This option requires a source term file for each blade row, defined by the GE STP Source Term Program pre-processor.
Type	Integer
Default	0	Maximum	None	Minimum	0

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transition

TURBO Source-code Name	trans
Description	Percent chord transition location on the suction surface in decimal fraction.
Type	Real
Default	0.0	Maximum	1.	Minimum	0.

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x_start_viscous_hub

TURBO Source-code Name	xst_vhc(1)
Description	Axial coordinate downstream of which a viscous boundary condition is applied to the hub. Upstream of this line a slip wall BC is applied.
Units	m
Type	Real
Default	-9999.	Maximum	none	Minimum	none

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x_start_viscous_case

TURBO Source-code Name	xst_vhc(2)
Description	Axial coordinate downstream of which a viscous boundary condition is applied to the casing. Upstream of this line a slip wall BC is applied.
Units	m
Type	Real
Default	-9999.	Maximum	none	Minimum	none

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x_start_hub_rotation

TURBO Source-code Name	xst_hc(1)
Description	Axial coordinate at which the hub rotation starts.
Units	m
Type	Real
Default	-9999.	Maximum	none	Minimum	none

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x_end_hub_rotation

TURBO Source-code Name	xend_hc(1)
Description	Axial coordinate at which the hub rotation ends.
Units	m
Type	Real
Default	9999.	Maximum	none	Minimum	none

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x_start_case_rotation

TURBO Source-code Name	xst_hc(2)
Description	Axial coordinate at which casing rotation starts.
Units	m
Type	Real
Default	9999.	Maximum	none	Minimum	none

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x_end_case_rotation

TURBO Source-code Name	xend_hc(2)
Description	Axial coordinate at which casing rotation ends
Units	m
Type	Real
Default	9999.	Maximum	none	Minimum	none

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blade_row_ksym

TURBO Source-code Name	ksym_br
Description	To capture upstream wake effects due to difference in pitch between alternating blade rows, more than one passage in the down-stream blade row may be needed when using the phase-lag approximation. This parameter can be used for this purpose. It acts as the symmetry factor parameter in a full simulation, except this is for individual blade row and has to be an integer.
Type	Integer
Default	nbld	Maximum	none	Minimum	1

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cut_plane_dir

TURBO Source-code Name	cut_dir
Description	Define the cutting plane direction; for option 5 output only.
Type	Integer (1=i, 2=j, 3=k)
Default	2	Maximum	3	Minimum	1

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num_cut_plane

TURBO Source-code Name	ncut
Description	Number of cutting planes.  When set to 0, series of grids and solutions in regular PLOT3D format are written.
Type	Integer
Default	0	Maximum	10	Minimum	0

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cut_plane_global_posi

TURBO Source-code Name	cut_posi
Description	Indices indicating locations of the cutting planes in the original grid (before partitioning).
Type	Integer array of dimension(10)
Default	1	Maximum	MAX	Minimum	1

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upstream_freq_only

TURBO Source-code Name	upfreq_only
Description	If this flag is checked only the disturbance from the upstream blade row is modeled.  The unsteady frequency is then reduced to the blade-passing frequency of this blade row. This option is useful to create initial time history data for phase-lag simulations. When the history becomes periodic in the reduced (upstream-only) mode, this flag should be turned off to recover unsteady disturbances from both sides.
Type	Logical
Default	False	Maximum	True	Minimum	False

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This page last modified: Thursday, July 3, 2003 5:02:06 PM.