Annotated Turbine B Input File

Annotated Input File for Turbine B

Comment lines in the input file

#, ! Any lines that start with these characters are ignored. Some lines may have comments at the end. Even these are ignored.

Parameters similar to those used in the PROP code

MODE 1.0
Mode of operation of the machine as a wind turbine.

LTIP 1.0
Use the Prandtl's tip loss model.

LHUB 1.0
Prandtl hub loss model is to be used.

IBR 1.0
Use the advanced brake model.

ISTL 1.0
Use the Viterna stall model in the post stall region.

USEAP 1.0
Include the swirl effects.

WEXP 0.0000
The exponent to be used in the boundary layer profile of the wind.

HH 3.372
Normalized tower height wrt rotor radius

NS_NSEC 10.0 1.0
Number of blade elements/number of sectors

IS1 1.0
First segment used in analysis

IS2 10.0
Last segment used in analysis

BE_DATA 0.0
Do not print out blade element data

INCV 0.0
Use Tip Speed Ratio

SH 0.0
Ignore shaft tilt effects on cross flow

BN 2.0
Number of blades in the rotor

CONE 4.00
Cone angle of rotor

RHO 0.002057
Density(slugs/ft^3)

HUB 0.07
Normalized hub radius (hub radius/rotor radius)

RD 43.00
Rotor radius (ft)

Blade Geometry Specification

CH_TW 0.01617 5.848 0.07507 5.393 0.08551 4.825 0.08670 4.008 0.08160 2.879 0.07560 1.762 0.06847 0.819 0.05981 0.254 0.04986 0.076 0.03672 0.027
This line indicates the method of specifying the normalized blade geometry. The normalized chord distribution and twist angle along span are given here. The number of points at which the distributions are given should be equal to the number of segments the blade is divided into in the NS_NSEC line. In this annotated input file, this line is not being used because the blade geometry is specified using the relative description above.

Stall Delay Models

DU_MODEL 1.0 1.0 1.0 27.25
Stall delay models to be used are indicated by these 2 lines. The UIUC model line, DU_MODEL, is followed by 4 inputs. The first 3 are the empirical constants in the model. Their best value is 1. The last value is the wind speed to be used in generating 3D data when using the model in the fixed wind speed mode (described with the AirfoilFileNames line).

The CORRIGAN_EXPN line indicates that the Corrigan model is to be used for stall delay. The value input in the line line is exponent to be used in the expression for the Corrigan model.

Note that the specification of the post stall models has to occur before the airfoil data is read in to the program by the AIRFOIL_MODE line. If neither model is used, then the program uses the stall delay angle specified in the AIRFOIL_MODE line and keeps the C_lmax fixed for this angle range before starting post stall models.

#CORRIGAN_EXPN 1

Lines related to obtaining airfoil data from the code in the variable wind mode

PROPFileNames 10 uiucseg1.dat turbine B at station 1 uiucseg2.dat turbine B at station 2 uiucseg3.dat turbine B at station 3 uiucseg4.dat turbine B at station 4 uiucseg5.dat turbine B at station 5 uiucseg6.dat turbine B at station 6 uiucseg7.dat turbine B at station 7 uiucseg8.dat turbine B at station 8 uiucseg9.dat turbine B at station 9 uiucseg10.dat turbine B at station 10
This line reads in the file names and titles to the files which are to be used to store the data generated in the variable wind mode. Variable wind mode means that the angles of attack are generated by using a wind sweep specified by the user in the analysis mode. As opposed to the variable wind mode, data can also be obtained from the code in a fixed wind mode, which is described with the AirfoilFileNames line.
For this input file, the UIUC model is on. The names of the data files are indicative of this. Note that when this line is used, the user must specify a file name and a title for each of the segments. In this input file, the blade is divided into 10 segments. Hence, 10 file names and titles are input. Since the data written to these files comes out of the analysis, this line must appear before the analysis lines in the input file.
Data written to this file is wind speed, angle of attack, lift coefficient, drag coefficient, lift increment due t the UIUC model if it is on and potential lift curve, 2 × pi × angle of attack which is used in the UIUC model.
The files generated by the PROPFileNames line can be downloaded here.

Airfoil specifications

AIRFOIL_MODE 3 6 ../polardata/airfoil2 0.21 10 0 1.2 5 0 30 ../polardata/airfoil2 0.21 10 0 1.2 5 0 30 ../polardata/airfoil1ext 0.21 15 0 1.1 5 0 30 ../polardata/airfoil3 0.16 12 0 1.0 5 0 30 ../polardata/airfoil3 0.16 12 0 1.0 5 0 30 ../polardata/CYLINDER.TXT 1.00 0.1 3 0.10 4 00 30
The mode 3 indicates that the airfoil data that follows is in the format of C_l, C_d and angle of attack. Mode 4 would indicate angle of attack, C_l and C_d. The number of airfoils which follow is being read in is indicated in the next line. The location of the airfoil is input in the next line. The airfoil parameters, viz, t/c ratio, stall angle, stall delay angle, C_lmax, insert angle for the Corrigan model, the start and end angles for the UIUC model are input for each airfoil. The line must occur after the stall delay models are specified.

AIRFOIL_FAMILY 6 0.00 6 1.0 0.05 1 0.85 0.30 2 0.40 0.75 3 0.20 0.95 4 0.05 1.00 5 0.00
This line indicates the distribution of airfoils along the blade span. The first column is the span wise location and the second column is the airfoil to be used from the AIRFOIL_MODE line. The airfoil properties at each segment along the blade are interpolated by using these airfoil distributions and the blending functions in the third column.

USE_AIRFOIL_FAMILY 1
If more than one airfoil family is described, then this line indicates which of those families is to be used for analysis.

Analysis Lines

TIPON
Makes sure that the tip loss model is always on

DP 1 57 1 999 2 Specifies a design point. The parameters input are the design point number, the rpm, pitch, wind speed and the units for the wind speed.

IDES Starts the design process.

RPM_DP 1 PITCH_DP 1 WIND_SWEEP 7 50.0 1 2.0 2D_SWEEP WRITE_FILES 40 45 55 95 100 50 RPM_DP 1 PITCH_DP 1 WIND_SWEEP 7 15 2 1 1D_SWEEP WRITE_FILES 35 75 85 90 80 95 99 32
This is the analysis mode to determine the rotor performance.
The files generated by the WRITE_FILES line can be downloaded here.

Lines related to obtaining data from the code in the fixed wind mode

StationRe 1 10 1 2 3 4 5 6 7 8 9 10
Airfoil data at particular blade segments w/ Re taken from previous analysis run. The number input after the StationRe line must be the same as that input after the AirfoilFileNames line. This is for data output for the fixed wind mode. The data can be obtained for any or all of the segments in this case, unlike the PROPFileNames line.

Fixed wind mode means that the airfoil data is generated at one wind speed, and there is an angle of attack sweep, similar to the wind tunnel situation.

AirfoilFileNames 10 uiucwfix1.dat turbine B at station 1 uiucwfix2.dat turbine B at station 2 uiucwfix3.dat turbine B at station 3 uiucwfix4.dat turbine B at station 4 uiucwfix5.dat turbine B at station 5 uiucwfix6.dat turbine B at station 6 uiucwfix7.dat turbine B at station 7 uiucwfix8.dat turbine B at station 8 uiucwfix9.dat turbine B at station 9 uiucwfix10.dat turbine B at station 10
These are the names of the output files and their titles for the fixed wind output. These lines must necessarily come before the MakePROPAirfoilData line because that line creates the data files and the file names have to be input before that line occurs in the input file.
The angle of attack and the lift coefficient is written to the file first, followed by the angle of attack and the drag coefficient. The angle of attack values are the sweep described in the AlfaMinMaxInc line.
The files generated by the AirfoilFileNames line can be downloaded here.

AlfaMinMaxInc 1 -10 50 2
This line gives the angle of attack sweep for generating data for the fixed wind mode. If 1 is used, then the next line contains the minimum, maximum and increment angles for the sweep. If 2 is used, then the actual angles are specified.

PrintHeaders This line is an indication to write out blade segment and the Re at that segment to screen

Itype 3 This line indicates the mode of the output from the PrintHeaders line. The mode 3 indicates that the airfoil data that is output is in the format of C_l, C_d and angle of attack. Mode 4 would indicate angle of attack, C_l and C_d.

MakePROPAirfoilData This line generates the output data for the fixed wind mode

#OUTPROP #turbb-prop.in
Files are written out in these two lines that are used as input files to PROP and AERODYN programs. The lines are followed by the name of the file desired. The OUTAERODYN feature is still not implemented.

#OUTAERODYN #turbb-aerodyn.in

Generate the PROP93 and PROPID output files (features not fully documented)

DUMP_PROP93 1 9
These two lines write out files which can be used for a PROP93 run and a PROPID input file respectively.

DUMP_PROPID 21

End of File

* This is the character that indicates the end of file. Everything after this character in the input file will be ignored by the program.

Annotated Input File for Turbine B
Comment lines in the input file
#, !	Any lines that start with these characters are ignored. Some lines may have comments at the end. Even these are ignored.




Parameters similar to those used in the PROP code
MODE 1.0	Mode of operation of the machine as a wind turbine.
LTIP 1.0	Use the Prandtl's tip loss model.
LHUB 1.0	Prandtl hub loss model is to be used.
IBR 1.0	Use the advanced brake model.
ISTL 1.0	Use the Viterna stall model in the post stall region.
USEAP 1.0	Include the swirl effects.
WEXP 0.0000	The exponent to be used in the boundary layer profile of the wind.
HH 3.372	Normalized tower height wrt rotor radius
NS_NSEC 10.0 1.0	Number of blade elements/number of sectors
IS1 1.0	First segment used in analysis
IS2 10.0	Last segment used in analysis
BE_DATA 0.0	Do not print out blade element data
INCV 0.0	Use Tip Speed Ratio
SH 0.0	Ignore shaft tilt effects on cross flow
BN 2.0	Number of blades in the rotor
CONE 4.00	Cone angle of rotor
RHO 0.002057	Density(slugs/ft^3)
HUB 0.07	Normalized hub radius (hub radius/rotor radius)
RD 43.00	Rotor radius (ft)




Blade Geometry Specification
CH_TW 0.01617 5.848 0.07507 5.393 0.08551 4.825 0.08670 4.008 0.08160 2.879 0.07560 1.762 0.06847 0.819 0.05981 0.254 0.04986 0.076 0.03672 0.027	This line indicates the method of specifying the normalized blade geometry. The normalized chord distribution and twist angle along span are given here. The number of points at which the distributions are given should be equal to the number of segments the blade is divided into in the `NS_NSEC` line. In this annotated input file, this line is not being used because the blade geometry is specified using the relative description above.




Stall Delay Models
DU_MODEL 1.0 1.0 1.0 27.25	Stall delay models to be used are indicated by these 2 lines. The UIUC model line, `DU_MODEL`, is followed by 4 inputs. The first 3 are the empirical constants in the model. Their best value is 1. The last value is the wind speed to be used in generating 3D data when using the model in the fixed wind speed mode (described with the `AirfoilFileNames` line). The `CORRIGAN_EXPN` line indicates that the Corrigan model is to be used for stall delay. The value input in the line line is exponent to be used in the expression for the Corrigan model. Note that the specification of the post stall models has to occur before the airfoil data is read in to the program by the `AIRFOIL_MODE` line. If neither model is used, then the program uses the stall delay angle specified in the `AIRFOIL_MODE` line and keeps the C_lmax fixed for this angle range before starting post stall models.
#CORRIGAN_EXPN 1




Lines related to obtaining airfoil data from the code in the variable wind mode
PROPFileNames 10 uiucseg1.dat turbine B at station 1 uiucseg2.dat turbine B at station 2 uiucseg3.dat turbine B at station 3 uiucseg4.dat turbine B at station 4 uiucseg5.dat turbine B at station 5 uiucseg6.dat turbine B at station 6 uiucseg7.dat turbine B at station 7 uiucseg8.dat turbine B at station 8 uiucseg9.dat turbine B at station 9 uiucseg10.dat turbine B at station 10	This line reads in the file names and titles to the files which are to be used to store the data generated in the variable wind mode. Variable wind mode means that the angles of attack are generated by using a wind sweep specified by the user in the analysis mode. As opposed to the variable wind mode, data can also be obtained from the code in a fixed wind mode, which is described with the `AirfoilFileNames` line. For this input file, the UIUC model is on. The names of the data files are indicative of this. Note that when this line is used, the user must specify a file name and a title for each of the segments. In this input file, the blade is divided into 10 segments. Hence, 10 file names and titles are input. Since the data written to these files comes out of the analysis, this line must appear before the analysis lines in the input file. Data written to this file is wind speed, angle of attack, lift coefficient, drag coefficient, lift increment due t the UIUC model if it is on and potential lift curve, 2 × pi × angle of attack which is used in the UIUC model. The files generated by the `PROPFileNames` line can be downloaded here.




Airfoil specifications
AIRFOIL_MODE 3 6 ../polardata/airfoil2 0.21 10 0 1.2 5 0 30 ../polardata/airfoil2 0.21 10 0 1.2 5 0 30 ../polardata/airfoil1ext 0.21 15 0 1.1 5 0 30 ../polardata/airfoil3 0.16 12 0 1.0 5 0 30 ../polardata/airfoil3 0.16 12 0 1.0 5 0 30 ../polardata/CYLINDER.TXT 1.00 0.1 3 0.10 4 00 30	The mode 3 indicates that the airfoil data that follows is in the format of C_l, C_d and angle of attack. Mode 4 would indicate angle of attack, C_l and C_d. The number of airfoils which follow is being read in is indicated in the next line. The location of the airfoil is input in the next line. The airfoil parameters, viz, t/c ratio, stall angle, stall delay angle, C_lmax, insert angle for the Corrigan model, the start and end angles for the UIUC model are input for each airfoil. The line must occur after the stall delay models are specified.
AIRFOIL_FAMILY 6 0.00 6 1.0 0.05 1 0.85 0.30 2 0.40 0.75 3 0.20 0.95 4 0.05 1.00 5 0.00	This line indicates the distribution of airfoils along the blade span. The first column is the span wise location and the second column is the airfoil to be used from the `AIRFOIL_MODE` line. The airfoil properties at each segment along the blade are interpolated by using these airfoil distributions and the blending functions in the third column.
USE_AIRFOIL_FAMILY 1	If more than one airfoil family is described, then this line indicates which of those families is to be used for analysis.




Analysis Lines
TIPON	Makes sure that the tip loss model is always on
`DP` `1 57 1 999 2`	Specifies a design point. The parameters input are the design point number, the rpm, pitch, wind speed and the units for the wind speed.
`IDES`	Starts the design process.
RPM_DP 1 PITCH_DP 1 WIND_SWEEP 7 50.0 1 2.0 2D_SWEEP WRITE_FILES 40 45 55 95 100 50 RPM_DP 1 PITCH_DP 1 WIND_SWEEP 7 15 2 1 1D_SWEEP WRITE_FILES 35 75 85 90 80 95 99 32	This is the analysis mode to determine the rotor performance. The files generated by the `WRITE_FILES` line can be downloaded here.




Lines related to obtaining data from the code in the fixed wind mode
StationRe 1 10 1 2 3 4 5 6 7 8 9 10	Airfoil data at particular blade segments w/ Re taken from previous analysis run. The number input after the `StationRe` line must be the same as that input after the `AirfoilFileNames` line. This is for data output for the fixed wind mode. The data can be obtained for any or all of the segments in this case, unlike the `PROPFileNames` line. Fixed wind mode means that the airfoil data is generated at one wind speed, and there is an angle of attack sweep, similar to the wind tunnel situation.
AirfoilFileNames 10 uiucwfix1.dat turbine B at station 1 uiucwfix2.dat turbine B at station 2 uiucwfix3.dat turbine B at station 3 uiucwfix4.dat turbine B at station 4 uiucwfix5.dat turbine B at station 5 uiucwfix6.dat turbine B at station 6 uiucwfix7.dat turbine B at station 7 uiucwfix8.dat turbine B at station 8 uiucwfix9.dat turbine B at station 9 uiucwfix10.dat turbine B at station 10	These are the names of the output files and their titles for the fixed wind output. These lines must necessarily come before the `MakePROPAirfoilData` line because that line creates the data files and the file names have to be input before that line occurs in the input file. The angle of attack and the lift coefficient is written to the file first, followed by the angle of attack and the drag coefficient. The angle of attack values are the sweep described in the `AlfaMinMaxInc` line. The files generated by the `AirfoilFileNames` line can be downloaded here.
AlfaMinMaxInc 1 -10 50 2	This line gives the angle of attack sweep for generating data for the fixed wind mode. If `1` is used, then the next line contains the minimum, maximum and increment angles for the sweep. If `2` is used, then the actual angles are specified.
`PrintHeaders`	This line is an indication to write out blade segment and the Re at that segment to screen
`Itype 3`	This line indicates the mode of the output from the `PrintHeaders` line. The mode 3 indicates that the airfoil data that is output is in the format of C_l, C_d and angle of attack. Mode 4 would indicate angle of attack, C_l and C_d.
`MakePROPAirfoilData`	This line generates the output data for the fixed wind mode
#OUTPROP #turbb-prop.in	Files are written out in these two lines that are used as input files to PROP and AERODYN programs. The lines are followed by the name of the file desired. The `OUTAERODYN` feature is still not implemented.
#OUTAERODYN #turbb-aerodyn.in




Generate the PROP93 and PROPID output files (features not fully documented)
DUMP_PROP93 1 9	These two lines write out files which can be used for a PROP93 run and a PROPID input file respectively.
DUMP_PROPID 21




End of File
*	This is the character that indicates the end of file. Everything after this character in the input file will be ignored by the program.