*******************************************
         *   PROPID Quick Reference Sheet 990801   *
         *               By Example                *
         *******************************************


******************************************************************************
# Basic input
MODE 1.0            # wind turbine
INCV 0.0            # wind turbine mode (use TSR in analysis)
LTIP 1.0            # use tip loss model
LHUB 1.0            # use hub loss model
IBR 1.0             # use brake state model
ISTL 1.0            # use viterna stall model
USEAP  1.0          # use swirl suppression
WEXP 0.0000         # boundary layer wind exponent
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 1           # printout blade element data
SH 0.0              # no shaft tilt effects on crossflow
RHO 0.0023769       # air density (slugs/ft^3)

# Geometry
HUB 0.04            # normalized hub cutout
HH 3.333            # normalized hub height
BN 3                # blade number
CONE 6.0            # cone angle of rotor (deg)
RD 24.61            # radius (ft)
CH_TW               # Normalized chord and twist distribution
   0.15       6
   0.13       6
   0.12       6
   0.11       6
   0.10       4
   0.09       2
   0.08       1
   0.07       0
   0.06      -1
   0.05      -2
******************************************************************************

******************************************************************************
# Corrigan stall model
CORRIGAN_EXPN 1

>>line> CORRIGAN_EXPN <EXPN> 
  # Used to turn on the Corrigan stall model and
  # EXPN is the exponent used by the model.  (See Corrigan paper -
  # Corrigan, J.J. and Schilling, J.J., "Empirical Model for Stall Delay
  # Due to Rotation," American Helicopter Society Aeromechanics
  # Specialists Conf., San Francisco, CA, Jan. 1994.) This line must come
  # before the airfoil data files are specified in the AIRFOIL_MODE line.
******************************************************************************


******************************************************************************
# Airfoil data lines
AIRFOIL_MODE    4
4
s814.pd
.24  13.  3  1.600  6 
s814.pd
.24  13.  3  1.600  6 
s812.pd
.21  14.3 3  1.180  6 
s813.pd
.16   9.  3  1.100  6 

>>line> AIRFOIL_MODE 4  #    airfoil data is in order of alfa, cl, cd
        <IAF>
        <AFFILE(1)>
        <AFTHK(1)>   <AFSTALL(1)>   <STDELAY(1)>  | -
        <CLMAXN(1)>   <ALINSERT(1)> | <DUSTART<1>> <DUEND<1>>
         ...
        <AFFILE(JAF)>
        <AFTHK(JAF)> <AFSTALL(JAF)> <STDELAY(JAF)>| -
        <CLMAXN(JAF)> <ALINSERT(JAF)> | <DUSTART<JAF>> <DUEND<JAF>>
        ...
        <AFFILE(IAF)>
        <AFTHK(IAF)> <AFSTALL(IAF)> <STDELAY(IAF)>| -
        <CLMAXN(IAF)> <ALINSERT(IAF)> | <DUSTART<IAF>> <DUEND<IAF>>

~~~~~~~~~~~~~~~~~~~~~

# airfoil family 1 with 4 airfoils
# r/R-location and airfoil index
AIRFOIL_FAMILY    4
     .0000   1
     .3000   2
     .7500   3
    1.0000   4

>>line> AIRFOIL_FAMILY  <KNODE(IAFMLY)>
        <AFX(IAFMLY,1)>             <IDXAF(IAFMLY,JNODE)>        |<BLENDDST(IAFMLY,JNODE)>
        ...
        <AFX(IAFMLY,JNODE)>         <IDXAF(IAFMLY,JNODE)>        |<BLENDDST(IAFMLY,JNODE)>
        ...
        <AFX(IAFMLY,KNODE(IAFMLY))> <IDXAF(IAFMLY,KNODE(IAFMLY))>|<BLENDDST(IAFMLY,KNODE(JNODE))>
# Several airfoil families can be used by adding more AIRFOIL_FAMILY lines.
# When using a stall delay model, an airfoil file specified by the AIRFOIL_MODE
# line should only be used once.

~~~~~~~~~~~~~~~~~~~~

# Sse the first airfoil family.
USE_AIRFOIL_FAMILY   1

line> USE_AIRFOIL_FAMILY <KAFMLY>  # indicates which airfoil family to use
******************************************************************************

******************************************************************************
# Tip loss models

# Enforce tip loss model to always be on
TIPON

# Use the Prandtl tip loss model,
# not the original modified model.
TIPMODE 2

# Use the original PROP model (a modified Prandtl model)
TIPMODE 1
******************************************************************************


******************************************************************************
# Design Points
# First design point(1): 64 rpm, 2 deg pitch, 15 mph
DP   1  64   2.00   15.000  2

>>line> DP <IDP> <RPMDP(IDP)> <FLDP(IDP)> <XJDP(IDP)> <IXDIMDP(IDP)>
      # design point line
      # IDP - design point number
      # RPMDP(.) - rpm, revs/minute
      # FLDP(.) - pitch angle, deg
      # XJDP(.) - speed
      # IXDIMDP(.) - dimensions of speed IXDIM   input dimension  
      #                                    0       ft/sec         
      #                                    1       m/sec          
      #                                    2       mph            
      #                                    3       tip speed ratio
******************************************************************************



******************************************************************************
# Initiate design (does some preliminary work before analysis)
# Also used to start iteration after a NEWT* line
IDES
******************************************************************************



******************************************************************************
# NEWT1* lines

# Use Newton iteration to prescribe the peak power
# One parameter prescribed via Newton iteration 
#            => "NEWT1"
# Peak Power => An Integrated quantity over a wind speed SWeeP
#            => "ISWP"
# 
NEWT1ISWP 300 95   25 50 1   1 1 999   1 1 999

>>line> NEWT1ISWP <IFTP1(.)> <FNEWT1(.)>  -
                  <XJSNT1(.)> <XJFNT1(.)> <DXJNT1(.)> -
                  <KDPRPM1(.)> <KDPFL1(.)> <KDPXJ1(.)> -
                  <ITP1(.)> <ITP2(.)>  <ITP3(.)> -
                  | <CLAMP1(.)> | <TOL1(.)>

# For example above
# type of variable = 300 for peak power prescription
# peak power = 95 kW
# start, end, inc in windspeed = 25, 50, 1 mph
# rpm, pitch design points = 1, 1, (999 dummy parameter)
# variable for iteration = 1, 1, (999 dummy parameter)
#                        = scale the rotor
# no clamp (step limit), no tolerance for automatic convergence


# Iterate on pitch to get cl(r/R=.75, station 8) = 1.00
NEWT1LDP 500 8 1.00   1 1 1   1 3 1   .75

>>line> NEWT1LDP <IFTP1(.)> <JSEGIX1(.)> <FNEWT1(.)> -
                 <KDPRPM1(.)> <KDPFL1(.)> <KDPXJ1(.)> -
                 <ITP1(.)> <ITP2(.)> <ITP3(.)> -
                 | <CLAMP1(.)> | <TOL1(.)>
******************************************************************************



******************************************************************************
# Iterate on twist to get cl 9-10
#>>line> NEWT2SDDP IFTP2(.) JSEGIX2(.) JSEGIX3(.) JSEGREL(.) KADJSBS(.)
#>>line> <SSS(1)> <SSF(1)>
#>>line> ...
#>>line> <SSS(KADJSBS(.))> <SSF(KADJSBS(.))>
#>>line> KDPRPM2(.) KDPFL2(.) KDPXJ2(.) ISDTP(.) ISCHED2(.) | CLAMP2(.) | TOL2(.)
#  Using --->      100 Cl dist
#                  101 a  dist
NEWT2SDDP 100   9 10 8   2
1 -.05
2 -.10
1 1 1   2 100   .75
******************************************************************************


******************************************************************************
# Special lines for variable speed turbines
LCOL45
VS_MODE

# Determine cp curve
PITCH_DP 1
TSR_SWEEP .5  14 .25
WIND_SWEEP 16  16  1  2
2D_SWEEP
# 45 - cp vs TSR
WRITE_FILES  45

# Determine the rotor power and thrust curves (2D_SWEEP)
FIXPD 500  1
PITCH_DP 1
TSR_SWEEP 6 6 0
WIND_SWEEP 5  50  1  2
2D_SWEEP
# write out 
# 40 - power curve (kW) vs wind speed (mph)
# 51 - rotor thrust curve
WRITE_FILES  40 51

# Obtain aero distributions along the blade (1D_SWEEP)
#
PITCH_DP 1
RPM_DP 1
WIND_DP 1
1D_SWEEP
# write out
# 75 - blade l/d  dist
# 76 - blade Re   dist
# 80 - blade alfa dist
# 85 - blade cl   dist
# 90 - blade a    dist
# 95 - chord dist (ft-ft)
# 99 - alfa  dist (ft-deg)
WRITE_FILES 75 76 80 85 90 95 99

# Annual energy production
GAEP  16 16 1 45
REPORT_START
# Report the last GAEP analysis case
REPORT_SPECIAL 8 999 999
REPORT_END

# Write out the rotor design parameters to file ftn021.dat
DUMP_PROPID
******************************************************************************