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AD/AA: Add new TE definition, improve airfoil thickness calculation, simplify input #597

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Feb 4, 2021
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AD/AA: Add new TE definition, improve airfoil thickness calculation, simplify input #597

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c06cc34
Merge pull request #10 from OpenFAST/dev
ptrbortolotti Aug 17, 2020
4887492
Merge pull request #11 from OpenFAST/dev
ptrbortolotti Nov 16, 2020
67a06dc
recode how rel thick is computed in TI Guidati
ptrbortolotti Nov 16, 2020
7ecc3a2
remove AAblade input file
ptrbortolotti Nov 18, 2020
ddbdd15
update docs aeroacoustics
ptrbortolotti Nov 19, 2020
64a2208
Get new TE definitions from r-test
rafmudaf Nov 20, 2020
3d9525b
Merge remote-tracking branch 'openfast/dev' into dev
rafmudaf Nov 20, 2020
45e0107
Merge branch 'dev' into pdev
rafmudaf Nov 20, 2020
939609d
Merge remote-tracking branch 'openfast/dev' into dev
rafmudaf Dec 9, 2020
1e5f066
Lturb and AvgV among inputs
ptrbortolotti Jan 7, 2021
0ff0690
update docs
ptrbortolotti Jan 7, 2021
c5020e6
Merge remote-tracking branch 'openfast/dev' into dev
rafmudaf Jan 7, 2021
7b58363
Update r-test
rafmudaf Jan 7, 2021
77441a2
Merge pull request #14 from ptrbortolotti/aa
ptrbortolotti Jan 7, 2021
61abddf
update r-test
ptrbortolotti Jan 7, 2021
db4ad43
correct wind speed to compute incident TI
ptrbortolotti Jan 7, 2021
c37fd3f
add Dbar for leading edge at high frequency
ptrbortolotti Jan 13, 2021
892c255
support TICalcMeth==2
ptrbortolotti Jan 27, 2021
7979169
Merge remote-tracking branch 'openfast/dev' into dev
rafmudaf Jan 27, 2021
e9f1e05
Merge remote-tracking branch 'openfast/dev' into dev
rafmudaf Feb 2, 2021
7ca24ac
Update AA regression test baselines
rafmudaf Feb 3, 2021
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62 changes: 22 additions & 40 deletions docs/source/user/aerodyn-aeroacoustics/App-usage.rst
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Original file line number Diff line number Diff line change
Expand Up @@ -97,12 +97,7 @@ models:
- **BluntMod** – Integer 0/1: flag to activate (**BluntMod=1**) the
trailing-edge bluntness – vortex shedding model, see :numref:`aa-TE-vortex`. If
the flag is set to 1, the trailing-edge geometry must be specified in
the file(s) listed in the field Blade Properties.

Next, the field Blade Properties lists three file names, often but not
necessarily identical, which contain the distributed properties
describing the detailed geometry of the trailing edge. These are
described in :numref:`aa-sec-TEgeom`.
the files as described in :numref:`aa-sec-BLinputs`.

The field Observer Locations contains the path to the file where the
number of observers (NrObsLoc) and the respective locations are
Expand Down Expand Up @@ -141,7 +136,7 @@ The file must be closed by an END command.

.. _aa-sec-BLinputs:

Boundary Layer Inputs
Boundary Layer Inputs and Trailing Edge Geometry
---------------------

When the flag **BLMod** is set equal to 2, pretabulated properties of the
Expand Down Expand Up @@ -188,6 +183,26 @@ outputs of XFoil. Because it is usually impossible to obtain these values for
the whole ranges of Reynolds numbers and angles of attack, the code is set to
adopt the last available values and print to screen a warning.

When the flag **BluntMod** is set to 1, the detailed geometry of the
trailing edge must also be defined along the span. Two inputs must be
provided, namely the angle, :math:`\Psi` between the suction and
pressure sides of the profile, right before the trailing-edge point, and
the height, :math:`h`, of the trailing edge. :math:`\Psi` must be
defined in degrees, while :math:`h` is in meters. Note that the BPM
trailing-edge bluntness model is very sensitive to these two parameters,
which, however, are often not easy to determine for real blades.
:numref:`aa-fig:GeomParamTE` shows the two inputs.

.. figure:: media/NoiseN011.png
:alt: Geometric parameters of the trailing-edge bluntness
:name: aa-fig:GeomParamTE
:width: 100.0%

Geometric parameters :math:`\mathbf{\Psi}` and
:math:`\mathbf{h}` of the trailing-edge bluntness

One value of :math:`\Psi` and one value of :math:`h` per file must be defined.
These values are not used if the flag **BluntMod** is set to 0.

.. container::
:name: aa-tab:AF20_BL
Expand Down Expand Up @@ -264,38 +279,5 @@ grid looks like the following:
:language: none


.. _aa-sec-TEgeom:

Trailing-Edge Geometry
----------------------

When the flag **BluntMod** is set to 1, the detailed geometry of the
trailing edge must be defined along the span. Two inputs must be
provided, namely the angle, :math:`\Psi,` between the suction and
pressure sides of the profile, right before the trailing-edge point, and
the height, :math:`h`, of the trailing edge. :math:`\Psi` must be
defined in degrees, while :math:`h` is in meters. Note that the BPM
trailing-edge bluntness model is very sensitive to these two parameters,
which, however, are often not easy to determine for real blades.
:numref:`aa-fig:GeomParamTE` shows the two inputs.

.. figure:: media/NoiseN011.png
:alt: Geometric parameters of the trailing-edge bluntness
:name: aa-fig:GeomParamTE
:width: 100.0%

Geometric parameters :math:`\mathbf{\Psi}` and
:math:`\mathbf{h}` of the trailing-edge bluntness

The two distributions must be defined with the same spanwise resolution
of the AeroDyn15 blade file, such as:

.. container::
:name: aa-tab:BladeProp

.. literalinclude:: example/BladeProp.dat
:linenos:
:language: none

.. [4]
https://github.com/OpenFAST/python-toolbox
138 changes: 71 additions & 67 deletions modules/aerodyn/src/AeroAcoustics.f90
View file
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Original file line number Diff line number Diff line change
Expand Up @@ -123,10 +123,10 @@ subroutine SetParameters( InitInp, InputFileData, p, ErrStat, ErrMsg )
CHARACTER(ErrMsgLen) :: ErrMsg2 ! temporary Error message if ErrStat / = ErrID_None
INTEGER(IntKi) :: ErrStat2 ! temporary Error status of the operation
INTEGER(IntKi) :: simcou,coun ! simple loop counter
INTEGER(IntKi) :: I,J,whichairfoil,K
INTEGER(IntKi) :: I,J,whichairfoil,K,i1_1,i10_1,i1_2,i10_2,iLE
character(*), parameter :: RoutineName = 'SetParameters'
LOGICAL :: tr,tri,exist
REAL(ReKi) :: val1,val2,f2,f4,lefttip,rightip,jumpreg
LOGICAL :: tr,tri,exist,LE_flag
REAL(ReKi) :: val1,val10,f2,f4,lefttip,rightip,jumpreg, dist1, dist10
! Initialize variables for this routine
ErrStat = ErrID_None
ErrMsg = ""
Expand Down Expand Up @@ -241,18 +241,19 @@ subroutine SetParameters( InitInp, InputFileData, p, ErrStat, ErrMsg )
call AllocAry(p%StallStart,p%NumBlNds,p%NumBlades,'p%StallStart',ErrStat2,ErrMsg2); if(Failed()) return
p%StallStart(:,:) = 0.0_ReKi

do i=1,p%NumBlades
p%TEThick(:,i) = InputFileData%BladeProps(i)%TEThick(:) !
p%TEAngle(:,i) = InputFileData%BladeProps(i)%TEAngle(:) !
do i=1,p%NumBlades
do j=1,p%NumBlNds
whichairfoil = p%BlAFID(j,i)
if(p%AFInfo(whichairfoil)%NumTabs /=1 ) then
call SetErrStat(ErrID_Fatal, 'Number of airfoil tables within airfoil file different than 1, which is not supported.', ErrStat2, ErrMsg2, RoutineName )
if(Failed()) return
endif
p%StallStart(j,i) = p%AFInfo(whichairfoil)%Table(1)%UA_BL%alpha1*180/PI ! approximate stall angle of attack [deg] (alpha1 in [rad])
whichairfoil = p%BlAFID(j,i)
p%TEThick(j,i) = InputFileData%BladeProps(whichairfoil)%TEThick
p%TEAngle(j,i) = InputFileData%BladeProps(whichairfoil)%TEAngle

if(p%AFInfo(whichairfoil)%NumTabs /=1 ) then
call SetErrStat(ErrID_Fatal, 'Number of airfoil tables within airfoil file different than 1, which is not supported.', ErrStat2, ErrMsg2, RoutineName )
if(Failed()) return
endif
p%StallStart(j,i) = p%AFInfo(whichairfoil)%Table(1)%UA_BL%alpha1*180/PI ! approximate stall angle of attack [deg] (alpha1 in [rad])
enddo
end do
enddo

call AllocAry(p%BlSpn, p%NumBlNds, p%NumBlades, 'p%BlSpn' , ErrStat2, ErrMsg2); if(Failed()) return
call AllocAry(p%BlChord, p%NumBlNds, p%NumBlades, 'p%BlChord', ErrStat2, ErrMsg2); if(Failed()) return
Expand Down Expand Up @@ -340,60 +341,63 @@ subroutine SetParameters( InitInp, InputFileData, p, ErrStat, ErrMsg )
if(Failed()) return
endif

! If simplified guidati is on, calculate the airfoil thickness from input airfoil coordinates
! If simplified guidati is on, calculate the airfoil thickness at 1% and at 10% chord from input airfoil coordinates
IF (p%IInflow .EQ. 2) THEN
! Calculate the Thickness @ 1% chord and @ 10% chord (normalized thickness)
call AllocAry(p%AFThickGuida,2,size(p%AFInfo), 'p%AFThickGuida', errStat2, errMsg2); if(Failed()) return
p%AFThickGuida=0.0_Reki

DO k=1,size(p%AFInfo) ! for each airfoil interpolation
tri=.true.;tr=.true.;
do i=2,size(p%AFInfo(k)%X_Coord)
if ( (p%AFInfo(k)%X_Coord(i)+p%AFInfo(k)%Y_Coord(i)) .eq. 0) then
!print*,i
goto 174
endif
if ( p%AFInfo(k)%X_Coord(i) .eq. 0.1) then
val1=p%AFInfo(k)%Y_Coord(i)
elseif ( (p%AFInfo(k)%X_Coord(i) .lt. 0.1) .and. (tri) ) then
val1=( abs(p%AFInfo(k)%X_Coord(i-1)-0.1)*p%AFInfo(k)%Y_Coord(i) + &
abs(p%AFInfo(k)%X_Coord(i)-0.1)*p%AFInfo(k)%Y_Coord(i-1))/ &
(abs(p%AFInfo(k)%X_Coord(i-1)-0.1)+abs(p%AFInfo(k)%X_Coord(i)-0.1))

tri=.false.
elseif (p%AFInfo(k)%X_Coord(i) .eq. 0.01) then
val2=p%AFInfo(k)%Y_Coord(i)
elseif ( (p%AFInfo(k)%X_Coord(i) .lt. 0.01) .and. (tr) ) then
val2=( abs(p%AFInfo(k)%X_Coord(i-1)-0.01)*p%AFInfo(k)%Y_Coord(i) + &
abs(p%AFInfo(k)%X_Coord(i)-0.01)*p%AFInfo(k)%Y_Coord(i-1))/ &
(abs(p%AFInfo(k)%X_Coord(i-1)-0.01)+abs(p%AFInfo(k)%X_Coord(i)-0.01))
tr=.false.
endif
enddo

174 tri=.true.;tr=.true.;
do j=i,size(p%AFInfo(k)%X_Coord)
if ( p%AFInfo(k)%X_Coord(j) .eq. 0.1) then
val1=abs(p%AFInfo(k)%Y_Coord(j)) + abs(val1)
elseif ( (p%AFInfo(k)%X_Coord(j) .gt. 0.1) .and. (tri) ) then
val1=abs(val1)+abs((abs(p%AFInfo(k)%X_Coord(j-1)-0.1)*p%AFInfo(k)%Y_Coord(j)+ &
abs(p%AFInfo(k)%X_Coord(j)-0.1)*p%AFInfo(k)%Y_Coord(j-1))/&
(abs(p%AFInfo(k)%X_Coord(j-1)-0.1)+abs(p%AFInfo(k)%X_Coord(j)-0.1)));
tri=.false.
elseif (p%AFInfo(k)%X_Coord(j) .eq. 0.01) then
val2=abs(p%AFInfo(k)%Y_Coord(j)) + abs(val2)
elseif ( (p%AFInfo(k)%X_Coord(j) .gt. 0.01) .and. (tr) ) then
val2=abs(val2)+abs((abs(p%AFInfo(k)%X_Coord(j-1)-0.01)*p%AFInfo(k)%Y_Coord(j)+ &
abs(p%AFInfo(k)%X_Coord(j)-0.01)*p%AFInfo(k)%Y_Coord(j-1))/&
(abs(p%AFInfo(k)%X_Coord(j-1)-0.01)+abs(p%AFInfo(k)%X_Coord(j)-0.01)));
tr=.false.
endif
enddo

p%AFThickGuida(1,k)=val2 ! 1 % chord thickness
p%AFThickGuida(2,k)=val1 ! 10 % chord thickness

! IF ((MIN(p%AFInfo(k)%X_Coord) < 0.) .or. (MAX(p%AFInfo(k)%X_Coord) > 0.)) THEN
! call SetErrStat ( ErrID_Fatal,'The coordinates of airfoil '//trim(num2lstr(k))//' are mot defined between x=0 and x=1. Code stops.' ,ErrStat, ErrMsg, RoutineName )
! ENDIF

! Flip the flag when LE is found and find index
LE_flag = .False.
DO i=3,size(p%AFInfo(k)%X_Coord)
IF (LE_flag .eqv. .False.) THEN
IF (p%AFInfo(k)%X_Coord(i) - p%AFInfo(k)%X_Coord(i-1) > 0.) THEN
LE_flag = .TRUE.
iLE = i
ENDIF
ENDIF
ENDDO

! From LE toward TE
dist1 = ABS( p%AFInfo(k)%X_Coord(iLE) - 0.01)
dist10 = ABS( p%AFInfo(k)%X_Coord(iLE) - 0.10)
DO i=iLE+1,size(p%AFInfo(k)%X_Coord)
IF (ABS(p%AFInfo(k)%X_Coord(i) - 0.01) < dist1) THEN
i1_1 = i
dist1 = ABS(p%AFInfo(k)%X_Coord(i) - 0.01)
ENDIF
IF (ABS(p%AFInfo(k)%X_Coord(i) - 0.1) < dist10) THEN
i10_1 = i
dist10 = ABS(p%AFInfo(k)%X_Coord(i) - 0.1)
ENDIF
ENDDO

! From TE to LE
dist1 = 0.99
dist10 = 0.90
DO i=1,iLE-1
IF (ABS(p%AFInfo(k)%X_Coord(i) - 0.01) < dist1) THEN
i1_2 = i
dist1 = ABS(p%AFInfo(k)%X_Coord(i) - 0.01)
ENDIF
IF (ABS(p%AFInfo(k)%X_Coord(i) - 0.1) < dist10) THEN
i10_2 = i
dist10 = ABS(p%AFInfo(k)%X_Coord(i) - 0.1)
ENDIF
ENDDO

val1 = p%AFInfo(k)%Y_Coord(i1_1) - p%AFInfo(k)%Y_Coord(i1_2)
val10 = p%AFInfo(k)%Y_Coord(i10_1) - p%AFInfo(k)%Y_Coord(i10_2)

p%AFThickGuida(1,k)=val1 ! 1 % chord thickness
p%AFThickGuida(2,k)=val10 ! 10 % chord thickness
ENDDO
ENDIF ! If simplified guidati is on, calculate the airfoil thickness
ENDIF

!! for turbulence intensity calculations on the fly every 5 meter the whole rotor area is divided vertically to store flow fields in each region
jumpreg=7
Expand Down Expand Up @@ -1063,8 +1067,8 @@ SUBROUTINE CalcAeroAcousticsOutput(u,p,m,xd,y,errStat,errMsg)
!--------Turbulent Boundary Layer Trailing Edge Noise----------------------------!
IF ( (p%ITURB .EQ. 1) .or. (p%ITURB .EQ. 2) ) THEN
CALL TBLTE(AlphaNoise,p%BlChord(J,I),UNoise,m%ChordAngleTE(K,J,I),m%SpanAngleTE(K,J,I), &
elementspan,m%rTEtoObserve(K,J,I), p, j,i,k,m%d99Var(2),m%dstarVar(1),m%dstarVar(2),p%StallStart(J,I), &
m%SPLP,m%SPLS,m%SPLALPH,m%SPLTBL,errStat2,errMsg2 )
elementspan,m%rTEtoObserve(K,J,I), p, j,i,k,m%d99Var(2),m%dstarVar(1),m%dstarVar(2),p%StallStart(J,I), &
m%SPLP,m%SPLS,m%SPLALPH,m%SPLTBL,errStat2,errMsg2 )
CALL SetErrStat( ErrStat2, ErrMsg2, ErrStat, ErrMsg, RoutineName )
IF (p%ITURB .EQ. 2) THEN
m%SPLP=0.0_ReKi;m%SPLS=0.0_ReKi;m%SPLTBL=0.0_ReKi;
Expand All @@ -1078,9 +1082,9 @@ SUBROUTINE CalcAeroAcousticsOutput(u,p,m,xd,y,errStat,errMsg)
!--------Blunt Trailing Edge Noise----------------------------------------------!
IF ( p%IBLUNT .EQ. 1 ) THEN
CALL BLUNT(AlphaNoise,p%BlChord(J,I),UNoise,m%ChordAngleTE(K,J,I),m%SpanAngleTE(K,J,I), &
elementspan,m%rTEtoObserve(K,J,I),p%TEThick(J,I),p%TEAngle(J,I), &
p, m%d99Var(2),m%dstarVar(1),m%dstarVar(2),m%SPLBLUNT,p%StallStart(J,I),errStat2,errMsg2 )
CALL SetErrStat( ErrStat2, ErrMsg2, ErrStat, ErrMsg, RoutineName )
elementspan,m%rTEtoObserve(K,J,I),p%TEThick(J,I),p%TEAngle(J,I), &
p, m%d99Var(2),m%dstarVar(1),m%dstarVar(2),m%SPLBLUNT,p%StallStart(J,I),errStat2,errMsg2 )
CALL SetErrStat( ErrStat2, ErrMsg2, ErrStat, ErrMsg, RoutineName )
ENDIF
!--------Tip Noise--------------------------------------------------------------!
IF ( (p%ITIP .EQ. 1) .AND. (J .EQ. p%NumBlNds) ) THEN
Expand Down Expand Up @@ -1445,7 +1449,7 @@ SUBROUTINE TBLTE(ALPSTAR,C,U,THETA,PHI,L,R,p,jj,ii,kk,d99Var2,dstarVar1,dstarVar

LOGICAL :: SWITCH !!LOGICAL FOR COMPUTATION OF ANGLE OF ATTACK CONTRIBUTION



ErrStat = ErrID_None
ErrMsg = ""
Expand Down
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