AD15: update units in nodal outputs Uin, Uit, Uir

OpenFAST · Jul 2, 2020 · cf611e3 · cf611e3
1 parent 17f8248
commit cf611e3
Show file tree

Hide file tree

Showing 3 changed files with 11 additions and 16 deletions.
diff --git a/docs/OtherSupporting/OutListParameters.xlsx b/docs/OtherSupporting/OutListParameters.xlsx
diff --git a/docs/source/user/aerodyn/examples/NodalOutputs.txt b/docs/source/user/aerodyn/examples/NodalOutputs.txt
@@ -51,8 +51,8 @@ END of input file (the word "END" must appear in the first 3 columns of this las
 "Cl_Static" - Static portion of lift force coefficient at each node, without  unsteady effects -- not available for BEMT/DBEMT
 "Cd_Static" - Static portion of drag force coefficient at each node, without unsteady effects -- not available for BEMT/DBEMT
 "Cm_Static" - Static portion of pitching moment coefficient at each node, without unsteady effects -- not available for BEMT/DBEMT
-"Uin"       - Axial induction in rotating hub coordinates. Axial aligned with hub axis.     rotor plane polar hub rotating coordinates
-"Uit"       - Tangential induction in rotating hub coordinates. Tangential to the rotation plane. Perpendicular to blade aziumth.     rotor plane polar hub rotating coordinates
-"Uir"       - Radial induction in rotating hub coordinates. Radial outwards in rotation plane. Aligned with blade azimuth.     rotor plane polar hub rotating coordinates
+"Uin"       - Axial induced velocity in rotating hub coordinates. Axial aligned with hub axis.     rotor plane polar hub rotating coordinates
+"Uit"       - Tangential induced velocity in rotating hub coordinates. Tangential to the rotation plane. Perpendicular to blade aziumth.     rotor plane polar hub rotating coordinates
+"Uir"       - Radial induced velocity in rotating hub coordinates. Radial outwards in rotation plane. Aligned with blade azimuth.     rotor plane polar hub rotating coordinates
 END of input file (the word "END" must appear in the first 3 columns of this last OutList line)
 ---------------------------------------------------------------------------------------
diff --git a/modules/aerodyn/src/AeroDyn_AllBldNdOuts_IO.f90 b/modules/aerodyn/src/AeroDyn_AllBldNdOuts_IO.f90
@@ -193,15 +193,14 @@ SUBROUTINE Calc_WriteAllBldNdOutput( p, u, m, y, OtherState, Indx, ErrStat, ErrM
 
          ! Precalculate the M_ph matrix -- no reason to recalculate for each output
       DO IdxBlade=1,p%NumBlades
-         psi_hub = TwoPi*(IdxBlade-1)/p%NumBlades
+         psi_hub = TwoPi*(real(IdxBlade-1,ReKi))/real(p%NumBlades,ReKi)
          M_ph(1,1:3) = (/ 1.0_ReKi, 0.0_ReKi    , 0.0_ReKi     /)
          M_ph(2,1:3) = (/ 0.0_ReKi, cos(psi_hub), sin(psi_hub) /)
          M_ph(3,1:3) = (/ 0.0_ReKi,-sin(psi_hub), cos(psi_hub) /)
          M_pg(1:3,1:3,IdxBlade) = matmul(M_ph, u%HubMotion%Orientation(1:3,1:3,1) ) 
       ENDDO
 
 
-
          ! Populate the header an unit lines for all blades and nodes
          ! First set a counter so we know where in the output array we are in
       OutIdx = p%NumOuts + 1       ! p%NumOuts is the number of outputs from the normal AeroDyn output.  The WriteOutput array is sized to p%NumOuts + num(AllBldNdOuts)
@@ -504,7 +503,7 @@ SUBROUTINE Calc_WriteAllBldNdOutput( p, u, m, y, OtherState, Indx, ErrStat, ErrM
                DO IdxBlade=1,p%BldNd_BladesOut
                   DO IdxNode=1,p%NumBlNds                   
 !NOT available in FVW yet
-!                     y%WriteOutput( OutIdx )  = m%Curve(IdxNode,IdxBlade)*R2D                                            
+                     y%WriteOutput( OutIdx ) = 0.0_ReKi 
                      OutIdx = OutIdx + 1
                   END DO
                END DO
@@ -848,7 +847,7 @@ SUBROUTINE Calc_WriteAllBldNdOutput( p, u, m, y, OtherState, Indx, ErrStat, ErrM
                DO IdxBlade=1,p%BldNd_BladesOut
                   DO IdxNode=1,p%NumBlNds
 !NOT available in FVW yet
-!                     y%WriteOutput( OutIdx )  =
+                     y%WriteOutput( OutIdx ) = 0.0_ReKi
                      OutIdx = OutIdx + 1
                   END DO
                END DO
@@ -892,7 +891,7 @@ SUBROUTINE Calc_WriteAllBldNdOutput( p, u, m, y, OtherState, Indx, ErrStat, ErrM
                DO IdxBlade=1,p%BldNd_BladesOut
                   DO IdxNode=1,u%BladeMotion(IdxBlade)%NNodes
 !NOT available in FVW yet
-!                     y%WriteOutput( OutIdx ) = m%BEMT_y%Cpmin(IdxNode,IdxBlade)
+                     y%WriteOutput( OutIdx ) = 0.0_ReKi
                      OutIdx = OutIdx + 1
                   ENDDO
                ENDDO
@@ -942,7 +941,7 @@ SUBROUTINE Calc_WriteAllBldNdOutput( p, u, m, y, OtherState, Indx, ErrStat, ErrM
                DO IdxBlade=1,p%BldNd_BladesOut
                   DO IdxNode=1,u%BladeMotion(IdxBlade)%NNodes
 !NOT available in BEMT/DBEMT yet
-!                     y%WriteOutput( OutIdx ) = 
+                     y%WriteOutput( OutIdx ) = 0.0_ReKi
                      OutIdx = OutIdx + 1
                   ENDDO
                ENDDO
@@ -961,7 +960,7 @@ SUBROUTINE Calc_WriteAllBldNdOutput( p, u, m, y, OtherState, Indx, ErrStat, ErrM
                DO IdxBlade=1,p%BldNd_BladesOut
                   DO IdxNode=1,u%BladeMotion(IdxBlade)%NNodes
 !NOT available in BEMT/DBEMT yet
-!                     y%WriteOutput( OutIdx ) = 
+                     y%WriteOutput( OutIdx ) = 0.0_ReKi
                      OutIdx = OutIdx + 1
                   ENDDO
                ENDDO
@@ -980,7 +979,7 @@ SUBROUTINE Calc_WriteAllBldNdOutput( p, u, m, y, OtherState, Indx, ErrStat, ErrM
                DO IdxBlade=1,p%BldNd_BladesOut
                   DO IdxNode=1,u%BladeMotion(IdxBlade)%NNodes
 !NOT available in BEMT/DBEMT yet
-!                     y%WriteOutput( OutIdx ) = 
+                     y%WriteOutput( OutIdx ) = 0.0_ReKi
                      OutIdx = OutIdx + 1
                   ENDDO
                ENDDO
@@ -1005,10 +1004,6 @@ SUBROUTINE Calc_WriteAllBldNdOutput( p, u, m, y, OtherState, Indx, ErrStat, ErrM
                      Vind_s = (/ -m%BEMT_u(Indx)%Vx(IdxNode,IdxBlade)*m%BEMT_y%axInduction(IdxNode,IdxBlade), m%BEMT_u(Indx)%Vy(IdxNode,IdxBlade)*m%BEMT_y%tanInduction(IdxNode,IdxBlade), 0.0_ReKi /)
                      Vind_g = matmul(Vind_s, m%WithoutSweepPitchTwist(:,:,IdxNode,IdxBlade))
                      y%WriteOutput( OutIdx ) = dot_product(M_pg(1,1:3,IdxBlade), Vind_g(1:3) ) ! Uihn, hub normal
-
-
-
-
                      OutIdx = OutIdx + 1
                   ENDDO
                ENDDO
@@ -1206,7 +1201,7 @@ SUBROUTINE BldNdOuts_SetOutParam(BldNd_OutList, p, ErrStat, ErrMsg )
                                "(-)    ","(-)    ","(-)    ","(-)    ","(-)    ","(deg)  ","(-)    ","(-)    ", &
                                "(Pa)   ","(N/m)  ","(N/m)  ","(N/m)  ","(N/m)  ","(N/m)  ","(N/m)  ","(m^2/s)", &
                                "(1/0)  ","(-)    ","(N-m/m)","(deg)  ","(-)    ","(-)    ","(-)    ","(m/s)  ", &
-                               "(m/s)  ","(m/s)  ","(deg)  ","(-)    ","(-)    ","(-)    ","(-)    ","(-)    ", &
+                               "(m/s)  ","(m/s)  ","(deg)  ","(-)    ","(-)    ","(m/s)  ","(m/s)  ","(m/s)  ", &
                                "(m/s)  ","(m/s)  ","(m/s)  ","(m/s)  ","(m/s)  ","(m/s)  ","(m/s)  ","(m/s)  ", &
                                "(m/s)  ","(m/s)  ","(m/s)  "/)