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AeroDyn cleanup #863

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Oct 21, 2021
Merged

AeroDyn cleanup #863

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5e22baa
Update comments in example AD airfoil files
bjonkman Oct 13, 2021
f43093e
AD: update error handling
bjonkman Oct 13, 2021
94fc94c
AD: replace instances of `Array(:)%Field` with loops: `Array(i)%Field`
bjonkman Oct 13, 2021
e4c8337
docs: Fix some typos
bjonkman Oct 11, 2021
c559faf
Merge remote-tracking branch 'NREL/dev' into b/AD_cleanup
bjonkman Oct 18, 2021
8f91c6f
AD: fix some error handling
bjonkman Oct 18, 2021
8e9c079
AD: destroy arrays in FileInfo type after use
bjonkman Oct 19, 2021
6df975e
docs: fix some typos/spelling errors
bjonkman Oct 20, 2021
872ef69
Added more error handling
bjonkman Oct 21, 2021
bbb38dd
update docs
bjonkman Oct 21, 2021
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2 changes: 1 addition & 1 deletion docs/source/user/aerodyn-aeroacoustics/index.rst
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Expand Up @@ -13,7 +13,7 @@ Aeroacoustics Noise Model of OpenFAST
fully open source and publicly available, is based on work performed
over the past three decades. Frequency-based models for turbulent
inflow; turbulent boundary layer – trailing edge; laminar boundary layer
–vortex shedding; tip vortex; and trailing edge bluntness – vortex
– vortex shedding; tip vortex; and trailing edge bluntness – vortex
shedding noise mechanisms are included. A simple directivity model is
also included.

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2 changes: 1 addition & 1 deletion docs/source/user/aerodyn-olaf/index.rst
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Expand Up @@ -12,7 +12,7 @@ OLAF User's Guide and Theory Manual (Free Vortex Wake in AeroDyn15)
releases are issued and as needed to provide further information on
advancements or modifications to the software.

The documentaiton here was derived from the OLAF users manual by K. Shaler,
The documentation here was derived from the OLAF users manual by K. Shaler,
E. Branlard, and A. Platt. (`https://www.nrel.gov/docs/fy20osti/75959.pdf
<https://www.nrel.gov/docs/fy20osti/75959.pdf>`_)

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5 changes: 4 additions & 1 deletion docs/source/user/aerodyn/appendix.rst
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Expand Up @@ -34,8 +34,9 @@ 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:`(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.
Expand All @@ -59,6 +60,7 @@ The local tower coordinate system is shown in :numref:`ad_tower_geom` and the lo
.. figure:: figs/ad_blade_local_cs.png
:width: 80%
:align: center
:alt: ad_blade_local_cs.png

AeroDyn Local Blade Coordinate System (Looking Toward the Tip,
from the Root) – l: Lift, d: Drag, m: Pitching, x: Normal (to Plane),
Expand All @@ -70,5 +72,6 @@ The local tower coordinate system is shown in :numref:`ad_tower_geom` and the lo
.. figure:: figs/ad_output_channel.pdf
:width: 500px
:align: center
:alt: ad_output_channel.pdf

AeroDyn Output Channel List
8 changes: 0 additions & 8 deletions docs/source/user/aerodyn/bibliography.bib
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Expand Up @@ -61,14 +61,6 @@ @techreport{Hansen:2004
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},
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2 changes: 1 addition & 1 deletion docs/source/user/aerodyn/driver.rst
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Expand Up @@ -9,7 +9,7 @@ A standalone AeroDyn driver is provided to perform aerodynamic simulations of ri
undergoing rigid body motion (fixed, sinusoidal, or arbitrary).
The standalone AeroDyn driver code improves on the functionality previously
available in the separate wind turbine rotor-performance tool WT\_Perf.
The driver alo supports turbine configurations that are not currently supported by OpenFAST.
The driver also supports turbine configurations that are not currently supported by OpenFAST.

Examples of applications are:

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81 changes: 42 additions & 39 deletions docs/source/user/aerodyn/examples/ad_airfoil_example.dat
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77 changes: 41 additions & 36 deletions docs/source/user/aerodyn/examples/ad_polar_example.dat
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Expand Up @@ -7,48 +7,53 @@
0.30 RelThickness - ! The non-dimensional thickness of the airfoil (thickness/chord) [only used if UAMod=7] [default=0.2] (-)
1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded)
@"DU30_A17_coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included.
"unused" BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called.
"unused" BL_file ! The file name including the boundary layer characteristics of the profile. Unused if the aeroacoustic module is not called.
1 NumTabs ! Number of airfoil tables in this file.
! ------------------------------------------------------------------------------
! data for table 1
! ------------------------------------------------------------------------------
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
!........................................
-2.2 alpha0 ! 0-lift angle of attack, depends on airfoil.
9 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg)
-9 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. (-)
7.3326 C_nalpha ! Slope of the 2D normal force coefficient curve. (1/rad)
3 T_f0 ! Initial value of the time constant associated with Df in the expression of Df and f''. [default = 3]
6 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 Re,M, and airfoil class. [default = 6]
1.7 T_p ! Boundary-layer,leading edge pressure gradient time constant in the expression of Dp. It should be tuned based on airfoil experimental data. [default = 1.7]
11 T_VL ! Initial value of the time constant associated with the vortex advection process; it represents the non-dimensional time in semi-chords, needed for a vortex to travel from LE to trailing edge (TE); it is used in the expression of Cvn. It depends on Re, M (weakly), and airfoil. [valid range = 6 - 13, default = 11]
0.14 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 for turbine airfoils. [from experimental results, defaults to 0.14]
0.53 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 for turbine airfoils. [from experimental results, defaults to 0.53]
5 b5 ! Constant in the expression of K'''_q,Cm_q^nc, and k_m,q. [from experimental results, defaults to 5]
0.3 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 for turbine airfoils. [from experimental results, defaults to 0.3]
0.7 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 for turbine airfoils. [from experimental results, defaults to 0.7]
1 A5 ! Constant in the expression of K'''_q,Cm_q^nc, and k_m,q. [from experimental results, defaults to 1]
0 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1]
0 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1]
0 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1]
0 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1]
1.449 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers.
-0.6138 Cn2 ! As Cn1 for negative AOAs.
0.19 St_sh ! Strouhal's shedding frequency constant. [default = 0.19]
0.008 Cd0 ! 2D drag coefficient value at 0-lift.
-0.09 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0]
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]
0.2 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]
!........................................
True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include UA coefficients below this line. Any missing coefficients will be calculated internally.
!........................................ > start of UA coefficients included only when InclUAdata=TRUE
!Note: If any of the following lines are missing, they will be calculated internally (they must be read in the following order, though)
-2.2 alpha0 ! 0-lift angle of attack, depends on airfoil. ! THIS IS AN OPTIONAL LINE; if omitted, it will be calculated from the polar data
9 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) [unused when UAMod=4|5] ! THIS IS AN OPTIONAL LINE; if omitted, it will be calculated from the polar data
-9 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA<alpha0. (deg) [unused when UAMod=4|5] ! 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]; it is set to 1 in the code when flookup=True. (-) [unused when UAMod=4|5] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to 1
7.3326 C_nalpha ! Slope of the 2D normal force coefficient curve. (1/rad) [unused when UAMod=4|5] ! THIS IS AN OPTIONAL LINE; if omitted, it will be calculated from the polar data
! 0 C_lalpha ! Maximum slope of the 2D lift force coefficient curve. (1/rad) [used only when UAMod=4] ! THIS IS AN OPTIONAL LINE; if omitted, it will be calculated from the polar data
3 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
6 T_V0 ! Initial value of the time constant associated with the vortex lift decay process. [default = 6] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
1.7 T_p ! Boundary-layer,leading edge pressure gradient time constant in the expression of Dp. [default = 1.7] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
11 T_VL ! Initial value of the time constant associated with the vortex advection process; [default = 11; unused when UAMod=4] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
0.14 b1 ! Constant in the expression of phi_alpha^c and phi_q^c (or x1_dot and x2_dot when UAMod=4|5). [default = 0.14] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
0.53 b2 ! Constant in the expression of phi_alpha^c and phi_q^c (or x1_dot and x2_dot when UAMod=4|5). [default = 0.53] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
5 b5 ! Constant in the expression of K'''_q,Cm_q^nc, and k_m,q. [defaults to 5; unused when UAMod = 4|5] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
0.3 A1 ! Constant in the expression of phi_alpha^c and phi_q^c (or x1_dot and x2_dot when UAMod=4|5). [default = 0.3] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
0.7 A2 ! Constant in the expression of phi_alpha^c and phi_q^c (or x1_dot and x2_dot when UAMod=4|5). [default = 0.7] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
1 A5 ! Constant in the expression of K'''_q,Cm_q^nc, and k_m,q. [default = 1]; unused when UAMod = 4|5] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
0 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [unused if UAMod<>1] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to 0
0 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [unused if UAMod<>1] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to 0
0 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [unused if UAMod<>1] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to 0
0 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [unused if UAMod<>1] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to 0
1.449 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. [unused when UAMod=4] ! THIS IS AN OPTIONAL LINE; if omitted, it will be calculated from the polar data
-0.6138 Cn2 ! As Cn1 for negative AOAs. [unused when UAMod=4] ! THIS IS AN OPTIONAL LINE; if omitted, it will be calculated from the polar data
0.19 St_sh ! Strouhal's shedding frequency constant. [default = 0.19; unused when UAMod = 4|5] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
0.008 Cd0 ! 2D drag coefficient value at 0-lift. ! THIS IS AN OPTIONAL LINE; if omitted, it will be calculated from the polar data
-0.09 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [unused when UAMod = 4|5] ! 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). [unused 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. [unused 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. [unused 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. [unused 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. [unused if UAMod<>1] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to 0
0.2 x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [unused 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). [Default = 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) [Default = 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|5] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
!........................................ < end of UA coefficients included only when InclUAdata=TRUE
! Table of aerodynamics coefficients
143 NumAlf ! Number of data lines in the following table
! Alpha Cl Cd Cm
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