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andrew-plattandrew-platt
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Merge pull request #3149 from bjonkman/b/AeroAcoustics_cleanup
AeroAcoustics cleanup + added driver code
2 parents 69cab72 + 2480d90 commit cd53c27

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‎modules/aerodyn/src/AeroAcoustics.f90‎

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‎modules/aerodyn/src/AeroAcoustics_Driver.f90‎

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!**********************************************************************************************************************************
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! LICENSING
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! Copyright (C) 2015-2016 National Renewable Energy Laboratory
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!
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! This file is part of AeroDyn.
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!
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! Licensed under the Apache License, Version 2.0 (the "License");
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! you may not use this file except in compliance with the License.
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! You may obtain a copy of the License at
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!
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! http://www.apache.org/licenses/LICENSE-2.0
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!
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! Unless required by applicable law or agreed to in writing, software
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! distributed under the License is distributed on an "AS IS" BASIS,
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! WITHOUT WARRANTIES OR CONDITIONS OF ANY KIND, either express or implied.
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! See the License for the specific language governing permissions and
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! limitations under the License.
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!
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!there will also be various control flags... this may be updated as needed:
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!TBLflag = {'BPM','TNO'}
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!bluntnessFlag = {'DTU','BPM'}
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!BPMBLflag = {'true','false'}
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!useOrigModelAtSepOnset = {'true','false'}
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!**********************************************************************************************************************************
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program AeroAcoustics_Driver
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use AeroAcoustics_Driver_Subs
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use VersionInfo
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implicit none
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! Program variables
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REAL(ReKi) :: PrevClockTime ! Clock time at start of simulation in seconds [(s)]
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REAL(ReKi) :: UsrTime1 ! User CPU time for simulation initialization [(s)]
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REAL(ReKi) :: UsrTime2 ! User CPU time for simulation (without initialization) [(s)]
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INTEGER(IntKi) , DIMENSION(1:8) :: StrtTime ! Start time of simulation (including initialization) [-]
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INTEGER(IntKi) , DIMENSION(1:8) :: SimStrtTime ! Start time of simulation (after initialization) [-]
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REAL(DbKi) :: t_global ! global-loop time marker
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REAL(DbKi) :: TiLstPrn ! The simulation time of the last print (to file) [(s)]
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TYPE(Dvr_Data) :: DriverData
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character(1024) :: InputFile
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integer :: nt !< loop counter (for time step)
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character(20) :: FlagArg ! flag argument from command line
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integer(IntKi) :: ErrStat ! status of error message
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character(ErrMsgLen) :: ErrMsg !local error message if ErrStat /= ErrID_None
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CALL DATE_AND_TIME ( Values=StrtTime ) ! Let's time the whole simulation
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CALL CPU_TIME ( UsrTime1 ) ! Initial time (this zeros the start time when used as a MATLAB function)
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UsrTime1 = MAX( 0.0_ReKi, UsrTime1 ) ! CPU_TIME: If a meaningful time cannot be returned, a processor-dependent negative value is returned
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UsrTime2 = UsrTime1 ! CPU_TIME: Initialize in case of error before getting real data
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SimStrtTime = StrtTime ! CPU_TIME: Initialize in case of error before getting real data
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nt = 0
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! --- Driver initialization
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CALL NWTC_Init( ProgNameIN=version%Name )
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InputFile = "" ! initialize to empty string to make sure it's input from the command line
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CALL CheckArgs( InputFile, Flag=FlagArg )
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IF ( LEN( TRIM(FlagArg) ) > 0 ) CALL NormStop()
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! Display the copyright notice and compile info:
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CALL DispCopyrightLicense( version%Name )
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CALL DispCompileRuntimeInfo( version%Name )
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! Initialize modules
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call ReadDriverInputFile( InputFile, DriverData, ErrStat, ErrMsg ); call CheckError()
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call Init_AFI(DriverData%Airfoil_FileName, DriverData%AFInfo, ErrStat, ErrMsg); call CheckError()
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call Init_AAmodule(DriverData, ErrStat, ErrMsg); call CheckError()
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! Init of time estimator
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t_global=0.0_DbKi
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call SimStatus_FirstTime( TiLstPrn, PrevClockTime, SimStrtTime, UsrTime2, t_global, DriverData%TMax )
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! Time loop
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do nt = 1, DriverData%numSteps
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! Time update to screen
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t_global=nt * DriverData%dt
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if (mod( nt + 1, 10 )==0) call SimStatus(TiLstPrn, PrevClockTime, t_global, DriverData%TMax)
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! update states and calculate output
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call SetInputsForAA(DriverData)
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call AA_CalcOutput(t_global, DriverData%u, DriverData%p, DriverData%xd, DriverData%OtherState, DriverData%y, DriverData%m, errStat, errMsg); call CheckError()
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call Dvr_WriteOutputs(t_global, nt, DriverData) ! write to file at this step
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! Get state variables at next step: INPUT at step nt - 1, OUTPUT at step nt
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call AA_UpdateStates(t_global, nt, DriverData%m, DriverData%u, DriverData%p, DriverData%xd, DriverData%OtherState, errStat, errMsg); call CheckError()
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end do !nt=1,numSteps
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call Dvr_End()
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contains
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!................................
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subroutine CheckError()
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if (ErrStat /= ErrID_None) then
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call WrScr(TRIM(errMsg))
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if (errStat >= AbortErrLev) then
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call Dvr_End()
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end if
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ErrStat = ErrID_None
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end if
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end subroutine CheckError
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!................................
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subroutine Dvr_End()
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integer(IntKi) :: errStat2 ! local status of error message
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character(ErrMsgLen) :: errMsg2 ! local error message if ErrStat /= ErrID_None
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call Dvr_EndOutput(DriverData, nt, errStat2, errMsg2)
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if (ErrStat2 /= ErrID_None) call WrScr(TRIM(errMsg2))
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call RunTimes(StrtTime, UsrTime1, SimStrtTime, UsrTime2, t_global)
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if (ErrStat >= AbortErrLev) then
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call WrScr('')
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CALL ProgAbort( 'AeroAcoustics Driver encountered simulation error level: '&
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//TRIM(GetErrStr(ErrStat)), TrapErrors=.FALSE., TimeWait=3._ReKi ) ! wait 3 seconds (in case they double-clicked and got an error)
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else
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call NormStop()
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end if
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end subroutine Dvr_End
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!................................
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end program AeroAcoustics_Driver
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!Inputs that will be supplied externally:
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!driver%DT
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!
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!Need to set in InitInput:
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! rho [InitInputType%airDens]
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! c0 or co [InitInputType%SpdSound]
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! L [InitInputType%BlSpn]
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! chord [InitInputType%BlChord]
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! [driver%DT = Interval]
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! visc [InitInputType%KinVisc]
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! [InitInputType%HubHeight]
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! Airfoil info:
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! BlAFID
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! AFInfo
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!
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!Set in AA Input File:
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! Lturb (already in AA input file) [InputFileData%Lturb]
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! dStarS [m%dstarVar(1), dstarVar1, DSTRS -> interpolated from p%dstarall1 = InputFileData%Suct_DispThick using AoA and Re] meters
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! dStarP [m%dstarVar(2), dstarVar2, DSTRP -> interpolated from p%dstarall2 = InputFileData%Pres_DispThick using AoA and Re] meters
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! TI [InputFileData%TI]
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! cfS [m%CfVar(1), Cfall(1) -> interpolated p%Cfall1=InputFileData%Suct_Cf with Re and AoA]
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! cfP [m%CfVar(2), Cfall(2) -> interpolated p%Cfall2=InputFileData%Pres_Cf with Re and AoA]
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! deltaS [m%d99Var(1) -> interpolated p%d99all1=InputFileData%Suct_BLThick with Re and AoA]
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! deltaP [m%d99Var(2), d99Var2 -> interpolated p%d99all2=InputFileData%Pres_BLThick with Re and AoA ] PRESSURE SIDE BOUNDARY LAYER THICKNESS METERS
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! uEdgeS [m%EdgeVelVar(1), EdgeVelAll(2) -> interpolated p%EdgeVelRat1=InputFileData%Suct_EdgeVelRat with Re and AoA]
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! uEdgeP [m%EdgeVelVar(2), EdgeVelAll(2) -> interpolated p%EdgeVelRat2=InputFileData%Pres_EdgeVelRat with Re and AoA]
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!
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!Inputs caluculated in AeroDyn (now set in driver input file?):
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! meanWindspeed [u%Inflow]
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! AoA [u%AoANoise]
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! [u%vRel]
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! [AeroCent_G] = u%BladeMotion(j)%Position(:,i) + u%BladeMotion(j)%TranslationDisp(:,i) (global position of the blade node) -> fixed value???
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! [RotGtoL] -> set to identity
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!
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!Inputs calculated
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! Ma [M or Mach] : calculated M = U / p%SpdSound ! MACH NUMBER
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! Re [RC] : calculated RC = U * C/p%KinVisc ! Reynolds number; C = chord; U=UNoise=sign( max(abs(u%Vrel(J,I)),0.1), u%Vrel(J,I) )
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!
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!fSep1p0_alpha (new to BPM)
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!fSpe0p7_alpha (new to BPM)
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