Merge branch 'f/driver-ua' into f/driver

docs/source/user/aerodyn/appendix.rst

@@ -25,7 +25,7 @@ outside of OpenFAST.
 
 
 3) AeroDyn Primary Input File 
-:download:`(primary input file example) <examples/ad_primary_example.inp>`: 
+:download:`(primary input file example) <examples/ad_primary_example.dat>`: 
 
 The primary AeroDyn input file defines modeling options, environmental conditions (except freestream flow), airfoils, tower nodal discretization and properties, as well as output file specifications.
 
@@ -34,12 +34,14 @@ The file is organized into several functional sections.  Each section correspond
 The input file begins with two lines of header information which is for your use, but is not used by the software.
 
 4) Airfoil Data Input File
-:download:`(airfoil data input file example) <examples/ad_airfoil_example.inp>`: 
+
+:download:`(profile data) <examples/ad_polar_example.dat>`: 
+:download:`(profile coordinates) <examples/ad_airfoil_example.dat>`: 
 
 The airfoil data input files themselves (one for each airfoil) include tables containing coefficients of lift force, drag force, and pitching moment versus AoA, as well as UA model parameters.  In these files, any line whose first non-blank character is an exclamation point (!) is ignored (for inserting comment lines).  The non-comment lines should appear within the file in order, but comment lines may be intermixed as desired for reading clarity.  
 
 5) Blade Data Input File
-:download:`(blade data input file example) <examples/ad_blade_example.inp>`: 
+:download:`(blade data input file example) <examples/ad_blade_example.dat>`: 
 
 The blade data input file contains the nodal discretization, geometry, twist, chord, and airfoil identifier for a blade.  Separate files are used for each blade, which permits modeling of aerodynamic imbalances.  
 

docs/source/user/aerodyn/bibliography.bib

@@ -0,0 +1,96 @@
+
+@TECHREPORT{AeroDyn:manual,
+    title       = {AeroDyn Theory Manual},
+    author      = {P. J. Moriarty and A. Craig Hansen},
+    institution = {National Renewable Energy Laboratory},
+    year        = 2005,
+    month       = {December},
+    note        = {NREL/EL-500-36881}
+}
+
+@TECHREPORT{AeroDyn:manualUnsteady,
+    title  = {The Unsteady Aerodynamics Module for FAST 8},
+    author = {R. Damiani and G. Hayman},
+    year   = 2019,
+    institution = {National Renewable Energy Laboratory},
+    note        = {NREL/TP-5000-66347}
+}
+
+@book{Branlard:book,
+    author = {E. Branlard},
+    title = {Wind Turbine Aerodynamics and Vorticity-Based Methods: Fundamentals and Recent Applications},
+    year = {2017},
+    publisher= {Springer International Publishing},
+    doi={10.1007/978-3-319-55164-7},
+    isbn={ 978-3-319-55163-0}
+}
+
+
+@article{Hansen:book,
+    author = {Hansen, M. O. L. and S{\o}rensen, J. N. and Voutsinas, S. and S{\o}rensen, N. and Madsen, H. Aa.},
+    doi = {10.1016/j.paerosci.2006.10.002},
+    journal = {Progress in Aerospace Sciences},
+    keywords = {aeroelasticity,wind turbines},
+    pages = {285--330},
+    title = {{State of the art in wind turbine aerodynamics and aeroelasticity}},
+    volume = {42},
+    year = {2006}
+}
+
+
+@article{Ning:2014,
+    author = {Ning, S. Andrew},
+    title = {A simple solution method for the blade element momentum equations with guaranteed convergence},
+    journal = {Wind Energy},
+    volume = {17},
+    number = {9},
+    pages = {1327-1345},
+    keywords = {blade element momentum equations, robust solution methodology, guaranteed convergence},
+    doi = {https://doi.org/10.1002/we.1636},
+    year = {2014}
+}
+
+
+@techreport{Hansen:2004,
+  title = {A Beddoes-Leishman type dynamic stall model in state-space and indicial formulations},
+  author = {Hansen, M.H. and Gaunaa, Mac and Aagaard Madsen, Helge},
+  year = {2004},
+  issn = {01062840},
+  isbn = {8755030904},
+  institution={Ris{\o} National Laboratory},
+  address={Roskilde, Denmark}
+}
+
+@techreport{Bladed:manual,
+  title = {Bladed Theory Manual version 4.8},
+  author = {DNV GL},
+  year = {2016},
+  institution={DNV-GL - Energy},
+  address={Bristol, UK}
+}
+
+
+@article{Oye:1991,
+    author = {S. {\O}ye},
+    title = {Dynamic stall, simulated as a time lag of separation},
+    year = {1991},
+    journal= {Proceedings of the 4th IEA Symposium on the Aerodynamics of Wind Turbines},
+    publisher={ETSU-N-118, Harwell Laboratory, UK}
+}
+
+@article{LeishmanBeddoes:1989,
+    author = {J. G. Leishman and T.S. Beddoes},
+    title = {A semi-empirical model for dynamic stall},
+    year = {1989},
+    journal= {Journal of the American Helicopter Society},
+    volume={34},
+    number={3},
+    pages={p3-17}
+}
+
+@techreport{Murray:2011,
+  title={The development of CACTUS : a wind and marine turbine performance simulation code.},
+  author={J. Murray and M. Barone},
+  year={2011},
+  institution={49th AIAA Aerospace Sciences Meeting, Orlando, Florida}
+}

docs/source/user/aerodyn/examples/ad_airfoil_example.inp → docs/source/user/aerodyn/examples/ad_airfoil_example.dat

@@ -86,40 +86,43 @@
 ! ------------------------------------------------------------------------------
        0.75   Re                ! Reynolds number in millions
           0   UserProp          ! User property (control) setting
-true          InclUAdata        ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line
+true          InclUAdata        ! Is unsteady aerodynamics data included in this table? If TRUE, then include UA coefficients below this line
 !........................................
-      -0.38   alpha0            ! 0-lift angle of attack, depends on airfoil.
-       15.3   alpha1            ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg)
-      -15.3   alpha2            ! Angle of attack at f=0.7, (approximately the stall angle) for AOA<alpha0. (deg)
-          1   eta_e             ! Recovery factor in the range [0.85 - 0.95] used only for UAMOD=1, it is set to 1 in the code when flookup=True. (-)
-    7.12499   C_nalpha          ! Slope of the 2D normal force coefficient curve. (1/rad)
-          2   T_f0              ! Initial value of the time constant associated with Df in the expression of Df and f''. [default = 3]
-          7   T_V0              ! Initial value of the time constant associated with the vortex lift decay process; it is used in the expression of Cvn. It depends on… 
-        1.6   T_p               ! Boundary-layer,leading edge pressure gradient time constant in the expression of Dp. It should be tuned based on airfoil experimental… 
-          9   T_VL              ! Initial value of the time constant associated with the vortex advection process; it represents the non-dimensional time in semi-…
-"Default"     b1                ! Constant in the expression of phi_alpha^c and phi_q^c.  This value is relatively insensitive for thin airfoils, but may be different… 
-"Default"     b2                ! Constant in the expression of phi_alpha^c and phi_q^c.  This value is relatively insensitive for thin airfoils, but may be different… 
-        0.5   b5                ! Constant in the expression of K'''_q,Cm_q^nc, and k_m,q.  [from  experimental results, defaults to 5]
-"Default"     A1                ! Constant in the expression of phi_alpha^c and phi_q^c.  This value is relatively insensitive for thin airfoils, but may be different… 
-"Default"     A2                ! Constant in the expression of phi_alpha^c and phi_q^c.  This value is relatively insensitive for thin airfoils, but may be different… 
-"Default"     A5                ! Constant in the expression of K'''_q,Cm_q^nc, and k_m,q. [from experimental results, defaults to 1]
-     18.269   S1                ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1]
-    -11.324   S2                ! Constant in the f curve best-fit for         AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1]
-     18.269   S3                ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1]
-    -11.324   S4                ! Constant in the f curve best-fit for         AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1]
-     1.9408   Cn1               ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It… 
-       -0.8   Cn2               ! As Cn1 for negative AOAs.
-"Default"     St_sh             ! Strouhal's shedding frequency constant.  [default = 0.19]
-     0.0016   Cd0               ! 2D drag coefficient value at 0-lift.
-    -0.0328   Cm0               ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does… 
-          0   k0                ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25).  [ignored if UAMod<>1]
-          0   k1                ! Constant in the \hat(x)_cp curve best-fit.  [ignored if UAMod<>1]
-          0   k2                ! Constant in the \hat(x)_cp curve best-fit.  [ignored if UAMod<>1]
-          0   k3                ! Constant in the \hat(x)_cp curve best-fit.  [ignored if UAMod<>1]
-          0   k1_hat            ! Constant in the expression of Cc due to leading edge vortex effects.  [ignored if UAMod<>1]
-"Default"     x_cp_bar          ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2]
-"DEFAULT"     UACutout          ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees]
-"DEFAULT"     filtCutOff        ! Reduced frequency cut-off for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (-) [default = 0.5]
+      -0.38   alpha0            ! 0-lift angle of attack, depends on airfoil. 										! THIS IS AN OPTIONAL LINE; if omitted, it will be calculated from the polar data
+       15.3   alpha1            ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg)	! THIS IS AN OPTIONAL LINE; if omitted, it will be calculated from the polar data
+      -15.3   alpha2            ! Angle of attack at f=0.7, (approximately the stall angle) for AOA<alpha0. (deg)	! THIS IS AN OPTIONAL LINE; if omitted, it will be calculated from the polar data
+          5   alphaUpper        ! Angle of attack at upper boundary of fully-attached region. (deg) [used only when UAMod=5] ! THIS IS AN OPTIONAL LINE; if omitted, it will be calculated from the polar data
+         -3   alphaLower        ! Angle of attack at lower boundary of fully-attached region. (deg) [used only when UAMod=5] ! THIS IS AN OPTIONAL LINE; if omitted, it will be calculated from the polar data 		   
+          1   eta_e             ! Recovery factor in the range [0.85 - 0.95] used only for UAMOD=1, it is set to 1 in the code when flookup=True. (-) 	! THIS IS AN OPTIONAL LINE; if omitted, it will be set to 1
+    7.12499   C_nalpha          ! Slope of the 2D normal force coefficient curve. (1/rad) 							! THIS IS AN OPTIONAL LINE; if omitted, it will be calculated from the polar data
+          2   T_f0              ! Initial value of the time constant associated with Df in the expression of Df and f''. [default = 3]	! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
+          7   T_V0              ! Initial value of the time constant associated with the vortex lift decay process; it is used in the expression of Cvn. ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value 
+        1.6   T_p               ! Boundary-layer,leading edge pressure gradient time constant in the expression of Dp. ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
+          9   T_VL              ! Initial value of the time constant associated with the vortex advection process; ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
+"Default"     b1                ! Constant in the expression of phi_alpha^c and phi_q^c.  ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
+"Default"     b2                ! Constant in the expression of phi_alpha^c and phi_q^c.  ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
+        0.5   b5                ! Constant in the expression of K'''_q,Cm_q^nc, and k_m,q.  [from  experimental results, defaults to 5; unused when UAMod = 4 or 5] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
+"Default"     A1                ! Constant in the expression of phi_alpha^c and phi_q^c.  ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
+"Default"     A2                ! Constant in the expression of phi_alpha^c and phi_q^c.  ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
+"Default"     A5                ! Constant in the expression of K'''_q,Cm_q^nc, and k_m,q. [from experimental results, defaults to 1; unused when UAMod = 4 or 5] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
+     18.269   S1                ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to 0
+    -11.324   S2                ! Constant in the f curve best-fit for         AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to 0
+     18.269   S3                ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to 0
+    -11.324   S4                ! Constant in the f curve best-fit for         AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1]  ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to 0
+     1.9408   Cn1               ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. ! THIS IS AN OPTIONAL LINE; if omitted, it will be calculated from the polar data
+       -0.8   Cn2               ! As Cn1 for negative AOAs. ! THIS IS AN OPTIONAL LINE; if omitted, it will be calculated from the polar data
+"Default"     St_sh             ! Strouhal's shedding frequency constant.  [default = 0.19; unused when UAMod = 4 or 5] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
+     0.0016   Cd0               ! 2D drag coefficient value at 0-lift. ! THIS IS AN OPTIONAL LINE; if omitted, it will be calculated from the polar data
+    -0.0328   Cm0               ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. ! THIS IS AN OPTIONAL LINE; if omitted, it will be calculated from the polar data
+          0   k0                ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25).  [ignored if UAMod<>1] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to 0
+          0   k1                ! Constant in the \hat(x)_cp curve best-fit.  [ignored if UAMod<>1] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to 0
+          0   k2                ! Constant in the \hat(x)_cp curve best-fit.  [ignored if UAMod<>1] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to 0
+          0   k3                ! Constant in the \hat(x)_cp curve best-fit.  [ignored if UAMod<>1] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to 0
+          0   k1_hat            ! Constant in the expression of Cc due to leading edge vortex effects.  [ignored if UAMod<>1]  ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to 0
+"Default"     x_cp_bar          ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
+"DEFAULT"     UACutout          ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
+"DEFAULT"     UACutout_delta    ! Delta angle of attack below UACutout where unsteady aerodynamics begin to turn off (blend with steady solution) (deg) [Specifying the string "Default" sets UACutout_delta to 5 degrees] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
+"DEFAULT"     filtCutOff        ! Reduced frequency cut-off for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (-) [default = 0.5; unused when UAMod = 4 or 5] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
 !........................................
 ! Table of aerodynamics coefficients
          63   NumAlf            ! Number of data lines in the following table