AD: change comments polar (p) -> local-polar (l)

OpenFAST · Jul 18, 2023 · e4b1542 · e4b1542
1 parent 5346b8a
commit e4b1542
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Showing 2 changed files with 13 additions and 13 deletions.
diff --git a/modules/aerodyn/src/AeroDyn_IO.f90 b/modules/aerodyn/src/AeroDyn_IO.f90
@@ -389,7 +389,7 @@ subroutine Calc_WriteOutput_BEMT()
          do j=1,u%BladeMotion(k)%NNodes
             !if(p%BEM_Mod==BEMMod_2D) then
             ! NOTE: if BEMMod_2D:   x & y are in "w" system (WithoutSweepPitchTwist)
-            !       if BEMMod_3D:   x & y are in "p" system (element polar system)
+            !       if BEMMod_3D:   x & y are in "l" system (local-polar system)
             Vind_s = (/ -m%BEMT_u(indx)%Vx(j,k)*m%BEMT_y%axInduction(j,k), m%BEMT_u(indx)%Vy(j,k)*m%BEMT_y%tanInduction(j,k), 0.0_ReKi /)
             m%Vind_i(:,j,k) = matmul(Vind_s, m%orientationAnnulus(:,:,j,k)) ! TODO rename orientationAnnulus
          enddo

diff --git a/modules/aerodyn/src/BEMTUncoupled.f90 b/modules/aerodyn/src/BEMTUncoupled.f90
@@ -129,7 +129,7 @@ subroutine GetRelativeVelocity( axInduction, tanInduction, Vx, Vy, cantAngle, xV
 
    end subroutine GetRelativeVelocity
 !..................................................................................................................................
-!> getAirfoilOrientation = R_ap = transformation from from polar coordinate system of the section to the airfoil coordinate system
+!> getAirfoilOrientation = R_al = transformation from from local-polar coordinate system of the section to the airfoil coordinate system
    subroutine getAirfoilOrientation( theta, cantAngle, toeAngle, afAxialVec, afNormalVec, afRadialVec )
       ! Routine for creating the airfoil orientation vectors
 
@@ -147,7 +147,7 @@ subroutine getAirfoilOrientation( theta, cantAngle, toeAngle, afAxialVec, afNorm
       orientation(1) = toeAngle
       orientation(2) = cantAngle
       orientation(3) = -theta
-      rotMat = EulerConstruct( orientation ) ! = R_ap: from polar to airfoil
+      rotMat = EulerConstruct( orientation ) ! = R_al: from local-polar to airfoil
 
       ! unit vector normal to the chord line in the airfoil plane
       afNormalVec = rotMat(1,:)
@@ -161,7 +161,7 @@ subroutine getAirfoilOrientation( theta, cantAngle, toeAngle, afAxialVec, afNorm
 
    end subroutine getAirfoilOrientation
 !..................................................................................................................................
-!> getAirfoilOrientation = R_ap = transformation from from polar coordinate system of the section to the airfoil coordinate system
+!> getAirfoilOrientation = R_al = transformation from from local-polar coordinate system of the section to the airfoil coordinate system
    subroutine getAirfoilOrientationMatrix( theta, cantAngle, toeAngle, rotMat)
       ! Routine for creating the airfoil orientation vectors
 
@@ -176,7 +176,7 @@ subroutine getAirfoilOrientationMatrix( theta, cantAngle, toeAngle, rotMat)
       orientation(1) = toeAngle
       orientation(2) = cantAngle
       orientation(3) = -theta
-      rotMat = EulerConstruct( orientation ) ! = R_ap: from polar to airfoil
+      rotMat = EulerConstruct( orientation ) ! = R_al: from local-polar to airfoil
    end subroutine getAirfoilOrientationMatrix
 !..................................................................................................................................
    subroutine computeAirfoilOperatingAOA( BEM_Mod, phi, theta, cantAngle, toeAngle, AoA )
@@ -263,8 +263,8 @@ subroutine Transform_ClCd_to_CxCy( phi, useAIDrag, useTIDrag, Cl, Cd, Cx, Cy )
 end subroutine Transform_ClCd_to_CxCy
 !----------------------------------------------------------------------------------------------------------------------------------
 !> Transform the aerodynamic coefficients (Cl,Cd,Cm) (directed based on Vrel_xy_a )
-!! from the airfoil coordinate system (a) to the polar coordinate system (p)
-!! NOTE: "Cy" is currently "-Cyp"
+!! from the airfoil coordinate system (a) to the local-polar coordinate system (l)
+!! NOTE: "Cy" is currently "-Cyl"
 subroutine Transform_ClCdCm_to_CxCyCzCmxCmyCmz( phi, theta, cant,toeAngle ,useAIDrag, useTIDrag, AOA, Cl, Cd, Cm, Cx, Cy, Cz, Cmx, Cmy, Cmz )
 
    implicit none
@@ -281,9 +281,9 @@ subroutine Transform_ClCdCm_to_CxCyCzCmxCmyCmz( phi, theta, cant,toeAngle ,useAI
    real(ReKi), intent(in   ) :: Cm
    real(ReKi), intent(  out) :: Cx, Cy, Cz
    real(ReKi), intent(  out) :: Cmx, Cmy, Cmz
-   real(ReKi)                :: afAxialVec(3)  !xhat_a_in_p
-   real(ReKi)                :: afNormalVec(3) !yhat_a_in_p
-   real(ReKi)                :: afRadialVec(3) !zhat_a_in_p
+   real(ReKi)                :: afAxialVec(3)  !xhat_a_in_l
+   real(ReKi)                :: afNormalVec(3) !yhat_a_in_l
+   real(ReKi)                :: afRadialVec(3) !zhat_a_in_l
    real(ReKi)                :: coeffVec(3)
    real(ReKi)                :: Cn
    real(ReKi)                :: Ct
@@ -307,9 +307,9 @@ subroutine Transform_ClCdCm_to_CxCyCzCmxCmyCmz( phi, theta, cant,toeAngle ,useAI
 
    ! Put force coefficients back into rotor plane reference frame
    coeffVec = Cn*afNormalVec + Ct*afAxialVec
-   Cx = coeffVec(1)   ! Cxp  and  cn
-   Cy = -coeffVec(2)  ! -Cyp      ct
-   Cz = coeffVec(3)   ! Czp
+   Cx = coeffVec(1)   !  Cxl  and  cn
+   Cy = -coeffVec(2)  ! -Cyl       ct
+   Cz = coeffVec(3)   !  Czl
 
    ! Put moment coefficients into the rotor reference frame
    coeffVec = Cm * afRadialVec