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TheodorsenAeroData Class Reference

#include <aerodata_impl.h>

Inheritance diagram for TheodorsenAeroData:
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Collaboration diagram for TheodorsenAeroData:
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Public Member Functions

 TheodorsenAeroData (int i_p, int i_dim, AeroData *pa, DriveCaller *ptime=0)
 
virtual ~TheodorsenAeroData (void)
 
virtual std::ostream & Restart (std::ostream &out) const
 
virtual void SetAirData (const doublereal &rho, const doublereal &c)
 
virtual void SetSectionData (const doublereal &abscissa, const doublereal &chord, const doublereal &forcepoint, const doublereal &velocitypoint, const doublereal &twist, const doublereal &omega=0.)
 
virtual unsigned int iGetNumDof (void) const
 
virtual DofOrder::Order GetDofType (unsigned int i) const
 
virtual void AssRes (SubVectorHandler &WorkVec, doublereal dCoef, const VectorHandler &XCurr, const VectorHandler &XPrimeCurr, integer iFirstIndex, integer iFirstSubIndex, int i, const doublereal *W, doublereal *TNG, outa_t &OUTA)
 
virtual void AssJac (FullSubMatrixHandler &WorkMat, doublereal dCoef, const VectorHandler &XCurr, const VectorHandler &XPrimeCurr, integer iFirstIndex, integer iFirstSubIndex, const Mat3xN &vx, const Mat3xN &wx, Mat3xN &fq, Mat3xN &cq, int i, const doublereal *W, doublereal *TNG, Mat6x6 &J, outa_t &OUTA)
 
virtual void AfterConvergence (int i, const VectorHandler &X, const VectorHandler &XP)
 
- Public Member Functions inherited from AeroData
 AeroData (int i_p, int i_dim, UnsteadyModel u=STEADY, DriveCaller *pt=0)
 
virtual ~AeroData (void)
 
std::ostream & RestartUnsteady (std::ostream &out) const
 
virtual int GetForces (int i, const doublereal *W, doublereal *TNG, outa_t &OUTA)
 
virtual int GetForcesJac (int i, const doublereal *W, doublereal *TNG, Mat6x6 &J, outa_t &OUTA)
 
AeroData::UnsteadyModel Unsteady (void) const
 
- Public Member Functions inherited from AeroMemory
 AeroMemory (DriveCaller *pt)
 
virtual ~AeroMemory (void)
 
void Predict (int i, doublereal alpha, doublereal &alf1, doublereal &alf2)
 
void Update (int i)
 
void SetNumPoints (int i)
 
int GetNumPoints (void) const
 

Protected Attributes

integer iParam
 
doublereal d14
 
doublereal d34
 
doublereal chord
 
doublereal a
 
doublereal A1
 
doublereal A2
 
doublereal b1
 
doublereal b2
 
doublereal * alpha_pivot
 
doublereal * dot_alpha_pivot
 
doublereal * dot_alpha
 
doublereal * ddot_alpha
 
doublereal * cfx_0
 
doublereal * cfy_0
 
doublereal * cmz_0
 
doublereal * clalpha
 
doublereal * prev_alpha_pivot
 
doublereal * prev_dot_alpha
 
doublereal prev_time
 
AeroData * pAeroData
 
- Protected Attributes inherited from AeroData
UnsteadyModel unsteadyflag
 
vam_t VAM
 
doublereal Omega
 
- Protected Attributes inherited from AeroMemory
DriveCaller * pTime
 

Additional Inherited Members

- Public Types inherited from AeroData
enum  UnsteadyModel { STEADY = 0, HARRIS = 1, BIELAWA = 2, LAST }
 
enum  {
  VX = 0, VY = 1, VZ = 2, WX = 3,
  WY = 4, WZ = 5, FX = 0, FY = 1,
  FZ = 2, MX = 3, MY = 4, MZ = 5
}
 
- Protected Member Functions inherited from AeroData
int StorageSize (void) const
 
int GetForcesJacForwardDiff_int (int i, const doublereal *W, doublereal *TNG, Mat6x6 &J, outa_t &OUTA)
 
int GetForcesJacCenteredDiff_int (int i, const doublereal *W, doublereal *TNG, Mat6x6 &J, outa_t &OUTA)
 

Detailed Description

Definition at line 156 of file aerodata_impl.h.

Constructor & Destructor Documentation

TheodorsenAeroData::TheodorsenAeroData ( int  i_p,
int  i_dim,
AeroData *  pa,
DriveCaller *  ptime = 0 
)

Definition at line 363 of file aerodata_impl.cc.

References ASSERT, AeroData::iGetNumDof(), pAeroData, AeroData::STEADY, and AeroData::Unsteady().

367 : AeroData(i_p, i_dim, STEADY, ptime),
368 iParam(0),
369 d14(0.), d34(0.),
370 chord(-1.),
371 a(0.),
372 A1(0.), A2(0.), b1(0.), b2(0.),
373 alpha_pivot(0), dot_alpha_pivot(0), dot_alpha(0), ddot_alpha(0),
374 cfx_0(0), cfy_0(0), cmz_0(0), clalpha(0),
375 prev_alpha_pivot(0), prev_dot_alpha(0),
376 prev_time(pTime->dGet()),
377 pAeroData(pa)
378 {
379  ASSERT(pAeroData->Unsteady() == STEADY);
380  ASSERT(pAeroData->iGetNumDof() == 0);
381 }
TheodorsenAeroData::alpha_pivot
doublereal * alpha_pivot
Definition: aerodata_impl.h:163
AeroData::iGetNumDof
virtual unsigned int iGetNumDof(void) const
Definition: aerodata.cc:362
TheodorsenAeroData::cfy_0
doublereal * cfy_0
Definition: aerodata_impl.h:164
TheodorsenAeroData::prev_dot_alpha
doublereal * prev_dot_alpha
Definition: aerodata_impl.h:166
TheodorsenAeroData::dot_alpha_pivot
doublereal * dot_alpha_pivot
Definition: aerodata_impl.h:163
TheodorsenAeroData::prev_time
doublereal prev_time
Definition: aerodata_impl.h:167
TheodorsenAeroData::ddot_alpha
doublereal * ddot_alpha
Definition: aerodata_impl.h:163
AeroData::Unsteady
AeroData::UnsteadyModel Unsteady(void) const
Definition: aerodata.cc:208
TheodorsenAeroData::dot_alpha
doublereal * dot_alpha
Definition: aerodata_impl.h:163
AeroMemory::pTime
DriveCaller * pTime
Definition: aerodata.h:67
TheodorsenAeroData::cmz_0
doublereal * cmz_0
Definition: aerodata_impl.h:164
TheodorsenAeroData::cfx_0
doublereal * cfx_0
Definition: aerodata_impl.h:164
TheodorsenAeroData::prev_alpha_pivot
doublereal * prev_alpha_pivot
Definition: aerodata_impl.h:166
TheodorsenAeroData::pAeroData
AeroData * pAeroData
Definition: aerodata_impl.h:169
ASSERT
#define ASSERT(expression)
Definition: colamd.c:977
DriveCaller::dGet
virtual doublereal dGet(const doublereal &dVar) const =0
TheodorsenAeroData::clalpha
doublereal * clalpha
Definition: aerodata_impl.h:165
AeroData::AeroData
AeroData(int i_p, int i_dim, UnsteadyModel u=STEADY, DriveCaller *pt=0)
Definition: aerodata.cc:181

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TheodorsenAeroData::~TheodorsenAeroData ( void  )
virtual

Definition at line 383 of file aerodata_impl.cc.

References alpha_pivot, pAeroData, SAFEDELETE, and SAFEDELETEARR.

384 {
385  if (alpha_pivot) {
386  SAFEDELETEARR(alpha_pivot);
387  }
388 
389  if (pAeroData) {
390  SAFEDELETE(pAeroData);
391  }
392 }
TheodorsenAeroData::alpha_pivot
doublereal * alpha_pivot
Definition: aerodata_impl.h:163
SAFEDELETEARR
#define SAFEDELETEARR(pnt)
Definition: mynewmem.h:713
TheodorsenAeroData::pAeroData
AeroData * pAeroData
Definition: aerodata_impl.h:169
SAFEDELETE
#define SAFEDELETE(pnt)
Definition: mynewmem.h:710

Member Function Documentation

void TheodorsenAeroData::AfterConvergence ( int  i,
const VectorHandler &  X,
const VectorHandler &  XP 
)
virtual

Reimplemented from AeroData.

Definition at line 914 of file aerodata_impl.cc.

References alpha_pivot, DriveCaller::dGet(), dot_alpha, prev_alpha_pivot, prev_dot_alpha, prev_time, and AeroMemory::pTime.

916 {
917  /* aggiorno i valori delle variabili per il calcolo
918  * della derivata attraverso le differenze finite */
919  prev_alpha_pivot[i] = alpha_pivot[i];
920  prev_dot_alpha[i] = dot_alpha[i];
921 
922  // same for all
923  prev_time = pTime->dGet();
924 }
TheodorsenAeroData::alpha_pivot
doublereal * alpha_pivot
Definition: aerodata_impl.h:163
TheodorsenAeroData::prev_dot_alpha
doublereal * prev_dot_alpha
Definition: aerodata_impl.h:166
TheodorsenAeroData::prev_time
doublereal prev_time
Definition: aerodata_impl.h:167
TheodorsenAeroData::dot_alpha
doublereal * dot_alpha
Definition: aerodata_impl.h:163
AeroMemory::pTime
DriveCaller * pTime
Definition: aerodata.h:67
TheodorsenAeroData::prev_alpha_pivot
doublereal * prev_alpha_pivot
Definition: aerodata_impl.h:166
DriveCaller::dGet
virtual doublereal dGet(const doublereal &dVar) const =0

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void TheodorsenAeroData::AssJac ( FullSubMatrixHandler &  WorkMat,
doublereal  dCoef,
const VectorHandler &  XCurr,
const VectorHandler &  XPrimeCurr,
integer  iFirstIndex,
integer  iFirstSubIndex,
const Mat3xN &  vx,
const Mat3xN &  wx,
Mat3xN &  fq,
Mat3xN &  cq,
int  i,
const doublereal *  W,
doublereal *  TNG,
Mat6x6 &  J,
outa_t &  OUTA 
)
virtual

Reimplemented from AeroData.

Definition at line 599 of file aerodata_impl.cc.

References a, A1, A2, grad::atan2(), b1, b2, c81_aerod2_u(), outa_t::cd, cfx_0, cfy_0, chord, outa_t::cl, clalpha, outa_t::cm, cmz_0, copysign(), d14, d34, ddot_alpha, vam_t::density, dot_alpha, dot_alpha_pivot, AeroData::GetForcesJac(), Mat3xN::iGetNumCols(), FullSubMatrixHandler::IncCoef(), M_PI, pAeroData, grad::pow(), Mat3xN::Put(), grad::sqrt(), grad::tan(), AeroData::unsteadyflag, AeroData::VAM, AeroData::VX, AeroData::VY, AeroData::VZ, AeroData::WX, AeroData::WY, and AeroData::WZ.

606 {
607 #ifdef DEBUG_JACOBIAN_UNSTEADY
608  doublereal q1 = XCurr(iFirstIndex + 1);
609  doublereal q2 = XCurr(iFirstIndex + 2);
610 #endif // DEBUG_JACOBIAN_UNSTEADY
611 
612  doublereal Uinf = sqrt(W[VX]*W[VX] + W[VY]*W[VY]);
613  doublereal d = 2*Uinf/chord;
614 #ifdef DEBUG_JACOBIAN_UNSTEADY
615  doublereal UUinf2 = Uinf*Uinf + W[VZ]*W[VZ];
616 #endif // DEBUG_JACOBIAN_UNSTEADY
617 #if 0
618  doublereal qD = .5*VAM.density*UUinf2;
619 #endif
620 
621  // doublereal u1 = atan2(- W[VY] - W[WZ]*d14, W[VX]);
622 #ifdef DEBUG_JACOBIAN_UNSTEADY
623  doublereal u2 = atan2(- W[VY] - W[WZ]*d34, W[VX]);
624 #endif // DEBUG_JACOBIAN_UNSTEADY
625 
626 #if 0
627  doublereal y1 = (A1 + A2)*b1*b2*d*d*q1 + (A1*b1 + A2*b2)*d*q2
628  + (1 - A1 - A2)*u2;
629 #endif
630 
631  WorkMat.IncCoef(iFirstSubIndex + 1, iFirstSubIndex + 1, 1.);
632  WorkMat.IncCoef(iFirstSubIndex + 2, iFirstSubIndex + 2, 1.);
633 
634  WorkMat.IncCoef(iFirstSubIndex + 1, iFirstSubIndex + 2, -dCoef);
635  WorkMat.IncCoef(iFirstSubIndex + 2, iFirstSubIndex + 1, dCoef*b1*b2*d*d);
636  WorkMat.IncCoef(iFirstSubIndex + 2, iFirstSubIndex + 2, dCoef*(b1 + b2)*d);
637 
638 #if 0
639  //if (Uinf > std::numeric_limits<doublereal>::epsilon()) {
640  if (Uinf > 1.e-2) {
641  /* computing the matrix g_{/\tilde{v}} - dimension: 2x3, where 2 is n_states */
642  doublereal dU_V_11, dU_V_12;
643 
644  doublereal dDen34 = W[VX]*W[VX] + W[VY]*W[VY] + W[WZ]*W[WZ]*d34*d34 + 2*W[VY]*W[WZ]*d34;
645 
646  dU_V_11 = (W[VY] + W[WZ]*d34)/dDen34;
647  dU_V_12 = -W[VX]/dDen34;
648 
649  doublereal dG_V_21, dG_V_22;
650 
651  dG_V_21 = (b1*b2*d*4*q1/chord + (b1+b2)*2*q2/chord)*W[VX]/Uinf - dU_V_11;
652  dG_V_22 = (b1*b2*d*4*q1/chord + (b1+b2)*2*q2/chord)*W[VY]/Uinf - dU_V_12;
653 
654 
655  /* computing the matrix g_{/\tilde{\omega}} - dimension: 2x3, where 2 is n_states */
656  doublereal dU_W_13;
657 
658  dU_W_13 = - W[VX]*d34/dDen34;
659 
660  doublereal dG_W_23;
661 
662  dG_W_23 = -dU_W_13;
663 
664  /* assembling the jacobian */
665  int iIndexColumn;
666  /* faccio i calcoli tenendo conto della sparsità della matrice g_{\/\tilde{v}} */
667  #if 1
668  for (iIndexColumn = 1; iIndexColumn <= vx.iGetNumCols(); iIndexColumn++){
669  WorkMat.IncCoef(iFirstSubIndex+2, iIndexColumn, dG_V_21*vx(1,iIndexColumn) + dG_V_22*vx(2,iIndexColumn));
670  WorkMat.IncCoef(iFirstSubIndex+2, iIndexColumn, dG_W_23*wx(3,iIndexColumn));
671  }
672  #endif
673  /* computing the matrix fq (f_a_{/q}) 3x2 */
674 
675  /* computing the derivative of the aerodynamic coefficient in the lookup table
676  * using the finite difference method */
677  /* perturbazione per calcolo delle derivare con le differenze finite */
678  doublereal dDeltaY1 = 1.*M_PI/180.;
679  doublereal y1d = y1 + dDeltaY1;
680  doublereal tan_y1 = std::tan(y1d);
681  doublereal Vxp2 = Uinf*Uinf - pow(W[VX]*tan_y1, 2) - std::pow(d34*W[WZ], 2);
682 
683  doublereal WW[6];
684  WW[VX] = copysign(std::sqrt(Vxp2), W[VX]);
685  WW[VY] = -W[VX]*tan_y1 - d34*W[WZ];
686  WW[VZ] = W[VZ];
687  WW[WX] = W[WX];
688  WW[WY] = W[WY];
689  WW[WZ] = W[WZ];
690 
691  c81_aerod2_u(WW, &VAM, TNG, &OUTA, const_cast<c81_data *>(data), unsteadyflag);
692  doublereal cx_1, cy_1, cmz_1;
693  if (qD > std::numeric_limits<doublereal>::epsilon()) {
694  cx_1 = OUTA.cd;
695  cy_1 = OUTA.cl;
696  cmz_1 = OUTA.cm;
697  }else{
698  cx_1 = 0.;
699  cy_1 = 0.;
700  cmz_1 = 0.;
701  }
702 
703  doublereal dCd_alpha = (cx_1-cfx_0[i])/dDeltaY1;
704  doublereal dCl_alpha = (cy_1-cfy_0[i])/dDeltaY1;
705  doublereal dCm_alpha = (cmz_1-cmz_0[i])/dDeltaY1;
706 
707  doublereal C11 = (A1+A2)*b1*b2*d*d;
708  doublereal C12 = (A1*b1+A2*b2)*d;
709 
710  doublereal qDc = qD*chord;
711  /* ATTENZIONE: le derivate aerodinamiche calcolate (vedi tecman)
712  * sono le dirivate di L D e M34 e vanno quindi routate per avere
713  * le derivate di TNG */
714  doublereal sin_alpha = (W[VY]+d34*W[WZ])/sqrt(W[VX]*W[VX]+W[VY]*W[VY]);
715  doublereal cos_alpha = (W[VX])/sqrt(W[VX]*W[VX]+W[VY]*W[VY]);
716 
717  doublereal D_q1 = qDc*dCd_alpha*C11;
718  doublereal D_q2 = qDc*dCd_alpha*C12;
719  doublereal L_q1 = qDc*dCl_alpha*C11;
720  doublereal L_q2 = qDc*dCl_alpha*C12;
721 
722  doublereal M_q1 = qDc*chord*dCm_alpha*C11;
723  doublereal M_q2 = qDc*chord*dCm_alpha*C12;
724  #if 0
725  fq.Put(1, 1, (-L_q1*sin_alpha -D_q1*cos_alpha));
726  fq.Put(1, 2, (-L_q2*sin_alpha -D_q2*cos_alpha));
727  fq.Put(2, 1, (L_q1*cos_alpha -D_q1*sin_alpha));
728  fq.Put(2, 2, (L_q2*cos_alpha -D_q2*sin_alpha));
729 
730  cq.Put(3, 1, (M_q1 +d14*fq(2,1)));
731  cq.Put(3, 2, (M_q2 +d14*fq(2,2)));
732  #endif
733  /* computing the J matrix */
734  /* f_{/\tilde{v}} */
735  doublereal dY_V_11, dY_V_12;
736 
737  /* (C_{/Uinf}*q + D_{/Uinf}*u)*Uinf_{v} */
738  dY_V_11 = (((A1+A2)*b1*b2*d*(4./chord)*q1 + (A1*b1+A2*b2)*(2./chord)*q2)*W[VX]/Uinf) + ((1-A1-A2)*dU_V_11);
739  dY_V_12 = (((A1+A2)*b1*b2*d*(4./chord)*q1 + (A1*b1+A2*b2)*(2./chord)*q2)*W[VY]/Uinf) + ((1-A1-A2)*dU_V_12);
740 
741  doublereal dCfy_Uinf = 0.5*clalpha[i]*(-dot_alpha_pivot[i] + (chord*a*ddot_alpha[i])/Uinf)/(d*Uinf);
742  doublereal rho = VAM.density;
743 
744  doublereal cy = cfy_0[i] + clalpha[i]/2/d*( dot_alpha_pivot[i] - a/d*ddot_alpha[i]);
745 
746  Mat6x6 Jaero = 0.;
747  Jaero(1,1) = rho*chord*cfx_0[i]*W[VX] + qDc*( dCd_alpha*dY_V_11);
748  Jaero(1,2) = rho*chord*cfx_0[i]*W[VY] + qDc*( dCd_alpha*dY_V_12);
749  Jaero(1,3) = rho*chord*cfx_0[i]*W[VZ];
750  Jaero(2,1) = rho*chord*cy*W[VX] + qDc*( dCl_alpha*dY_V_11 + dCfy_Uinf*W[VX]/Uinf);
751  Jaero(2,2) = rho*chord*cy*W[VY] + qDc*( dCl_alpha*dY_V_12 + dCfy_Uinf*W[VY]/Uinf );
752  Jaero(2,3) = rho*chord*cy*W[VZ];
753  Jaero(3,1) = rho*chord*cfz_0*W[VX];
754  Jaero(3,1) = rho*chord*cfz_0*W[VY];
755  Jaero(3,3) = rho*chord*cfz_0*W[VZ];
756 
757  /* f_{/\tilde{omega}} */
758  Jaero(1,6) = qDc*dCd_alpha*(1.-A1-A2)*dU_W_13;
759  Jaero(2,6) = qDc*dCl_alpha*(1.-A1-A2)*dU_W_13;
760 
761  /* c_{/\tilde{v}} */
762  doublereal dCmz_Uinf = 0.5*clalpha[i]*(dot_alpha_pivot[i] - ( ((chord*a)/(Uinf)) - ((chord)/(4*Uinf)) )*ddot_alpha[i] + dot_alpha[i])/(d*4*Uinf);
763 
764  doublereal cmz = cmz_0 + clalpha[i]/2/d*(-dot_alpha_pivot[i]/4 + (a/4/d - 1/d/16)*ddot_alpha[i] - dot_alpha[i]/4);
765 
766  Jaero(4,1) = rho*chord*chord*cmx_0*W[VX];
767  Jaero(4,2) = rho*chord*chord*cmx_0*W[VY];
768  Jaero(4,3) = rho*chord*chord*cmx_0*W[VZ];
769  Jaero(5,1) = rho*chord*chord*cmy_0*W[VX];
770  Jaero(5,2) = rho*chord*chord*cmy_0*W[VY];
771  Jaero(5,3) = rho*chord*chord*cmy_0*W[VZ];
772  Jaero(6,1) = rho*chord*chord*cmz*W[VX] +qDc*chord*( dCm_alpha*dY_V_11 + dCmz_Uinf*W[VX]/Uinf );
773  Jaero(6,2) = rho*chord*chord*cmz*W[VY] +qDc*chord*( dCm_alpha*dY_V_12 + dCmz_Uinf*W[VY]/Uinf );
774  Jaero(6,3) = rho*chord*chord*cmz*W[VZ];
775 
776  /* c_{/\tilde{omega}} */
777  Jaero(6,6) = qDc*chord*dCm_alpha*(1.-A1-A2)*dU_W_13;
778 
779  /* Jaero è lo jacobiano delle forze aerodinamiche L, D e M34
780  * occorre ruotarlo per avere lo jacobiano corretto J.
781  * Solo le righe 1 2 e 6 sono coivolte nella rotazione */
782  J = Jaero;
783  /* calcolo le forze aerodinamiche */
784  doublereal Drag = qDc*cfx_0[i];
785  doublereal Lift = qDc*cfy_0[i] + qDc*clalpha[i]/2/d*(dot_alpha_pivot[i] - a/d*ddot_alpha[i]);
786  /* calcolo le derivate del cos e sen dell'angolo di rotazione */
787  doublereal den = (W[VX]*W[VX]+W[VY]*W[VY])*sqrt((W[VX]*W[VX]+W[VY]*W[VY]));
788  doublereal sin_alpha_vx = -W[VX]*(W[VY]+d34*W[WZ])/den;
789  doublereal sin_alpha_vy = ( W[VX]*W[VX] - d34*W[WZ]*W[VY] )/den;
790  doublereal sin_alpha_wz = d34/sqrt(W[VX]*W[VX]+W[VY]*W[VY]);
791  doublereal cos_alpha_vx = ( W[VY]*W[VY] )/den;
792  doublereal cos_alpha_vy = -( W[VX]*W[VY] )/den;
793  #if 1
794  J(1,1) = -Jaero(2,1)*sin_alpha -Jaero(1,1)*cos_alpha - Lift*sin_alpha_vx - Drag*cos_alpha_vx;
795  J(1,2) = -Jaero(2,2)*sin_alpha -Jaero(1,2)*cos_alpha - Lift*sin_alpha_vy - Drag*cos_alpha_vy;
796  J(1,3) = -Jaero(2,3)*sin_alpha -Jaero(1,3)*cos_alpha;
797  J(1,6) = -Jaero(2,6)*sin_alpha -Jaero(1,6)*cos_alpha - Lift*sin_alpha_wz;
798 
799  J(2,1) = Jaero(2,1)*cos_alpha -Jaero(1,1)*sin_alpha + Lift*cos_alpha_vx - Drag*sin_alpha_vx;
800  J(2,2) = Jaero(2,2)*cos_alpha -Jaero(1,2)*sin_alpha + Lift*cos_alpha_vy - Drag*sin_alpha_vy;
801  J(2,3) = Jaero(2,3)*cos_alpha -Jaero(1,3)*sin_alpha;
802  J(2,6) = Jaero(2,6)*cos_alpha -Jaero(1,6)*sin_alpha - Drag*sin_alpha_wz;
803 
804  J(6,1) = Jaero(6,1) + d14*J(2,1);
805  J(6,2) = Jaero(6,2) + d14*J(2,2);
806  J(6,3) = Jaero(6,3) + d14*J(2,3);
807  J(6,4) = d14*J(2,4);
808  J(6,5) = d14*J(2,5);
809  J(6,6) = Jaero(6,6) + d14*J(2,6);
810  #endif
811  }
812 #endif
813 #ifdef DEBUG_JACOBIAN_UNSTEADY
814  printf("G/v matrix\n");
815  printf("%lf %lf %lf\n", 0., 0., 0.);
816  printf("%lf %lf %lf\n", dG_V_21, dG_V_22, 0.);
817 
818  printf("G/w matrix\n");
819  printf("%lf %lf %lf\n", 0., 0., 0.);
820  printf("%lf %lf %lf\n", 0., 0., dG_W_23);
821 
822  printf("f/q matrix\n");
823  printf("%lf %lf \n", fq(1,1), fq(1,2));
824  printf("%lf %lf \n", fq(2,1), fq(2,2));
825  printf("%lf %lf \n", 0., 0.);
826 
827  printf("c/q matrix\n");
828  printf("%lf %lf\n", 0., 0.);
829  printf("%lf %lf\n", 0., 0.);
830  printf("%lf %lf\n", cq(3,1), cq(3,2));
831 
832  printf("J matrix\n");
833  for( int iii=1; iii<=6; iii++){
834  for( int jjj=1; jjj<=6; jjj++){
835  printf("%lf ", J(iii,jjj));
836  }
837  printf("\n");
838  }
839 
840  FILE *fd;
841  fd = fopen("X.mat","w");
842  printf("DATI X\n");
843  for( int iii=1; iii<=2; iii++){
844  printf("%lf ", XCurr(iFirstIndex+iii));
845  fprintf(fd,"%15.7e ", XCurr(iFirstIndex+iii));
846  }
847  fclose(fd);
848  fd = fopen("XP.mat","w");
849  printf("\n");
850  printf("DATI XP\n");
851  for( int iii=1; iii<=2; iii++){
852  printf("%lf ", XPrimeCurr(iFirstIndex+iii));
853  fprintf(fd,"%15.7e ", XPrimeCurr(iFirstIndex+iii));
854  }
855  printf("\n");
856  fclose(fd);
857  fd = fopen("W.mat","w");
858  printf("DATI W\n");
859  printf("%lf %lf %lf %lf %lf %lf", W[VX], W[VY], W[VZ], W[WX], W[WY], W[WZ]);
860  fprintf(fd,"%15.7e %15.7e %15.7e %15.7e %15.7e %15.7e", W[VX], W[VY], W[VZ], W[WX], W[WY], W[WZ]);
861  fclose(fd);
862  printf("\n");
863  printf("PARAMETRI \n");
864  printf("d14 %lf ", d14);
865  printf("\nd34 %lf ", d34);
866  printf("\nA1 %lf ", A1);
867  printf("\nA2 %lf ", A2);
868  printf("\nb1 %lf ", b1);
869  printf("\nb2 %lf ", b2);
870  printf("\nchord %lf ", chord);
871  printf("\na %lf ", a);
872  printf("\nrho %lf ", rho);
873  printf("\ncfx_0 %lf ", cfx_0[i]);
874  fd = fopen("cfx_0.mat","w");
875  fprintf(fd,"%15.7e", cfx_0[i]);
876  fclose(fd);
877  printf("\ncfy_0 %lf ", cfy_0[i]);
878  fd = fopen("cfy_0.mat","w");
879  fprintf(fd,"%15.7e ", cfy_0[i]);
880  fclose(fd);
881  printf("\ncmz_0 %lf ", cmz_0[i]);
882  printf("\ndCl_alpha %lf ", dCl_alpha);
883  fd = fopen("dCl_alpha.mat","w");
884  fprintf(fd,"%15.7e", dCl_alpha);
885  fclose(fd);
886  printf("\ndCd_alpha %lf", dCd_alpha);
887  fd = fopen("dCd_alpha.mat","w");
888  fprintf(fd,"%15.7e", dCd_alpha);
889  fclose(fd);
890  printf("\ndCm_alpha %lf", dCm_alpha);
891  printf("\nclalpha %lf ", clalpha[i]);
892  printf("\n q1 q2 i %lf %lf %d", q1, q2, i);
893  fd = fopen("ddot_alpha.mat","w");
894  fprintf(fd,"%15.7e", ddot_alpha[i]);
895  printf("%lf", ddot_alpha[i]);
896  fclose(fd);
897  fd = fopen("dot_alpha.mat","w");
898  fprintf(fd,"%15.7e", dot_alpha[i]);
899  printf("%lf", dot_alpha[i]);
900  fclose(fd);
901  fd = fopen("dot_alpha_pivot.mat","w");
902  fprintf(fd,"%15.7e", dot_alpha_pivot[i]);
903  printf("%lf", dot_alpha_pivot[i]);
904  fclose(fd);
905  getchar();
906 #endif /* DEBUG_JACOBIAN_UNSTEADY */
907 
908  pAeroData->GetForcesJac(i, W, TNG, J, OUTA);
909 
910  // probably, we need to reset fq, cq
911 }
outa_t::cd
doublereal cd
Definition: aerodc81.h:66
vam_t::density
doublereal density
Definition: aerodc81.h:108
M_PI
#define M_PI
Definition: gradienttest.cc:67
grad::pow
GradientExpression< BinaryExpr< FuncPow, LhsExpr, RhsExpr > > pow(const GradientExpression< LhsExpr > &u, const GradientExpression< RhsExpr > &v)
Definition: gradient.h:2961
AeroData::GetForcesJac
virtual int GetForcesJac(int i, const doublereal *W, doublereal *TNG, Mat6x6 &J, outa_t &OUTA)
Definition: aerodata.cc:384
Mat3xN::Put
void Put(int i, integer j, const doublereal &d)
Definition: matvec3n.h:306
AeroData::VAM
vam_t VAM
Definition: aerodata.h:117
TheodorsenAeroData::cfy_0
doublereal * cfy_0
Definition: aerodata_impl.h:164
c81_aerod2_u
int c81_aerod2_u(doublereal *W, const vam_t *VAM, doublereal *TNG, outa_t *OUTA, c81_data *data, long unsteadyflag)
Definition: aerodc81.c:243
FullSubMatrixHandler::IncCoef
void IncCoef(integer iRow, integer iCol, const doublereal &dCoef)
Definition: submat.h:683
TheodorsenAeroData::dot_alpha_pivot
doublereal * dot_alpha_pivot
Definition: aerodata_impl.h:163
TheodorsenAeroData::ddot_alpha
doublereal * ddot_alpha
Definition: aerodata_impl.h:163
TheodorsenAeroData::dot_alpha
doublereal * dot_alpha
Definition: aerodata_impl.h:163
TheodorsenAeroData::cmz_0
doublereal * cmz_0
Definition: aerodata_impl.h:164
copysign
doublereal copysign(doublereal x, doublereal y)
Definition: gradient.h:97
outa_t::cl
doublereal cl
Definition: aerodc81.h:65
TheodorsenAeroData::cfx_0
doublereal * cfx_0
Definition: aerodata_impl.h:164
AeroData::unsteadyflag
UnsteadyModel unsteadyflag
Definition: aerodata.h:116
TheodorsenAeroData::pAeroData
AeroData * pAeroData
Definition: aerodata_impl.h:169
Mat3xN::iGetNumCols
integer iGetNumCols(void) const
Definition: matvec3n.h:298
grad::sqrt
GradientExpression< UnaryExpr< FuncSqrt, Expr > > sqrt(const GradientExpression< Expr > &u)
Definition: gradient.h:2974
TheodorsenAeroData::clalpha
doublereal * clalpha
Definition: aerodata_impl.h:165
outa_t::cm
doublereal cm
Definition: aerodc81.h:67
grad::atan2
GradientExpression< BinaryExpr< FuncAtan2, LhsExpr, RhsExpr > > atan2(const GradientExpression< LhsExpr > &u, const GradientExpression< RhsExpr > &v)
Definition: gradient.h:2962
doublereal
double doublereal
Definition: colamd.c:52
grad::tan
GradientExpression< UnaryExpr< FuncTan, Expr > > tan(const GradientExpression< Expr > &u)
Definition: gradient.h:2979

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void TheodorsenAeroData::AssRes ( SubVectorHandler &  WorkVec,
doublereal  dCoef,
const VectorHandler &  XCurr,
const VectorHandler &  XPrimeCurr,
integer  iFirstIndex,
integer  iFirstSubIndex,
int  i,
const doublereal *  W,
doublereal *  TNG,
outa_t &  OUTA 
)
virtual

Reimplemented from AeroData.

Definition at line 435 of file aerodata_impl.cc.

References a, A1, A2, alpha_pivot, grad::atan2(), b1, b2, vam_t::bc_position, outa_t::cd, cfx_0, cfy_0, vam_t::chord, chord, outa_t::cl, outa_t::clalpha, clalpha, outa_t::cm, cmz_0, copysign(), d14, d34, ddot_alpha, vam_t::density, DriveCaller::dGet(), dot_alpha, dot_alpha_pivot, vam_t::force_position, AeroData::GetForces(), AeroMemory::GetNumPoints(), iParam, MBDYN_EXCEPT_ARGS, pAeroData, grad::pow(), prev_alpha_pivot, prev_dot_alpha, prev_time, AeroMemory::pTime, VectorHandler::PutCoef(), SAFENEWARR, grad::sqrt(), grad::tan(), TheodorsenParams, AeroData::VAM, AeroData::VX, AeroData::VY, AeroData::VZ, AeroData::WX, AeroData::WY, and AeroData::WZ.

441 {
442  // FIXME: should do it earlier
443  if (alpha_pivot == 0) {
444  doublereal *d = 0;
445  SAFENEWARR(d, doublereal, 10*GetNumPoints());
446 
447 #ifdef HAVE_MEMSET
448  memset(d, '0', 10*GetNumPoints()*sizeof(doublereal));
449 #else // ! HAVE_MEMSET
450  for (int i = 0; i < 10*GetNumPoints(); i++) {
451  d[i] = 0.;
452  }
453 #endif // ! HAVE_MEMSET
454 
455  alpha_pivot = d;
456  d += GetNumPoints();
457  dot_alpha_pivot = d;
458  d += GetNumPoints();
459  dot_alpha = d;
460  d += GetNumPoints();
461  ddot_alpha = d;
462  d += GetNumPoints();
463  cfx_0 = d;
464  d += GetNumPoints();
465  cfy_0 = d;
466  d += GetNumPoints();
467  cmz_0 = d;
468  d += GetNumPoints();
469  clalpha = d;
470  d += GetNumPoints();
471  prev_alpha_pivot = d;
472  d += GetNumPoints();
473  prev_dot_alpha = d;
474  d += GetNumPoints();
475  }
476 
477  doublereal q1 = XCurr(iFirstIndex + 1);
478  doublereal q2 = XCurr(iFirstIndex + 2);
479 
480  doublereal q1p = XPrimeCurr(iFirstIndex + 1);
481  doublereal q2p = XPrimeCurr(iFirstIndex + 2);
482 
483  d14 = VAM.force_position;
484  d34 = VAM.bc_position;
485  if (std::abs(d34 - d14) < std::numeric_limits<doublereal>::epsilon()) {
486  silent_cerr("TheodorsenAeroData::AssRes() [#" << i << "]: aerodynamic center and boundary condition point are almost coincident" << std::endl);
487  throw ErrGeneric(MBDYN_EXCEPT_ARGS);
488  }
489  chord = VAM.chord;
490 
491  a = (d14 + d34)/chord;
492 
493  //doublereal Uinf = sqrt(W[VX]*W[VX] + W[VY]*W[VY]);
494  doublereal Uinf = sqrt(W[VX]*W[VX] + (W[VY]+d34*W[WZ])*(W[VY]+d34*W[WZ]));
495 
496  A1 = TheodorsenParams[iParam][0];
497  A2 = TheodorsenParams[iParam][1];
498  b1 = TheodorsenParams[iParam][2];
499  b2 = TheodorsenParams[iParam][3];
500 
501  doublereal u1 = atan2(- W[VY] - W[WZ]*d14, W[VX]);
502  doublereal u2 = atan2(- W[VY] - W[WZ]*d34, W[VX]); //deve essere l'incidenza a 3/4 corda!!!
503 
504  doublereal d = 2*Uinf/chord;
505 
506  doublereal y1 = (A1 + A2)*b1*b2*d*d*q1 + (A1*b1 + A2*b2)*d*q2
507  + (1 - A1 - A2)*u2;
508 
509  doublereal tan_y1 = std::tan(y1);
510  doublereal Vxp2 = Uinf*Uinf - pow(W[VX]*tan_y1, 2)
511  - std::pow(d34*W[WZ], 2);
512 
513  doublereal WW[6];
514  WW[VX] = copysign(std::sqrt(Vxp2), W[VX]);
515  //WW[VY] = -W[VX]*tan_y1 - d34*W[WZ];
516  WW[VY] = -WW[VX]*tan_y1 - d34*W[WZ];
517  WW[VZ] = W[VZ];
518  WW[WX] = W[WX];
519  WW[WY] = W[WY];
520  WW[WZ] = W[WZ];
521 
522  pAeroData->GetForces(i, WW, TNG, OUTA);
523 
524  doublereal UUinf2 = Uinf*Uinf + W[VZ]*W[VZ];
525  doublereal qD = .5*VAM.density*UUinf2;
526  if (qD > std::numeric_limits<doublereal>::epsilon()) {
527  cfx_0[i] = OUTA.cd;
528  cfy_0[i] = OUTA.cl;
529 #if 0
530  cfz_0 = 0.;
531  cmx_0 = 0.;
532  cmy_0 = 0.;
533 #endif
534  cmz_0[i] = OUTA.cm;
535  } else {
536  cfx_0[i] = 0.;
537  cfy_0[i] = 0.;
538 #if 0
539  cfz_0 = 0.;
540  cmx_0 = 0.;
541  cmy_0 = 0.;
542 #endif
543  cmz_0[i] = 0.;
544  }
545 
546  alpha_pivot[i] = (u1*d34 - u2*d14)/(d34 - d14);
547  dot_alpha[i] = Uinf*((u1 - u2)/(d34 - d14));
548 
549  doublereal Delta_t = pTime->dGet() - prev_time;
550  /* controllo che dovrebbe servire solo al primo istante di
551  * di tempo, in cui non calcolo le derivate per differenze
552  * finite per non avere 0 a denominatore. */
553  if (Delta_t > std::numeric_limits<doublereal>::epsilon()) {
554  dot_alpha_pivot[i] = (alpha_pivot[i] - prev_alpha_pivot[i])/Delta_t;
555  ddot_alpha[i] = (dot_alpha[i] - prev_dot_alpha[i])/Delta_t;
556 
557  } else {
558  dot_alpha_pivot[0] = 0.;
559  ddot_alpha[0] = 0.;
560  }
561 
562  clalpha[i] = OUTA.clalpha;
563  if (clalpha[i] > 0.) {
564  //if (Uinf > std::numeric_limits<doublereal>::epsilon()) {
565  if (Uinf > 1.e-5) {
566  doublereal cl = OUTA.cl + clalpha[i]/2/d*(dot_alpha_pivot[i] - a/d*ddot_alpha[i]);
567  doublereal cd = OUTA.cd;
568  doublereal cm = OUTA.cm + clalpha[i]/2/d*(-dot_alpha_pivot[i]/4 + (a/4/d - 1/d/16)*ddot_alpha[i] - dot_alpha[i]/4);
569  doublereal v[3], vp;
570  v[0] = W[0];
571  v[1] = W[1] + d34*W[5];
572  v[2] = W[2] - d34*W[4];
573  vp = sqrt(v[0]*v[0] + v[1]*v[1]);
574  TNG[0] = -qD*chord*(cl*v[1] + cd*v[0])/vp;
575  TNG[1] = qD*chord*(cl*v[0] - cd*v[1])/vp;
576  TNG[5] = qD*chord*chord*cm + d14*TNG[1];
577  } else {
578  TNG[0] = 0.;
579  TNG[1] = 0.;
580  TNG[2] = 0.;
581  TNG[3] = 0.;
582  TNG[4] = 0.;
583  TNG[5] = 0.;
584  }
585  } else {
586  TNG[0] = 0.;
587  TNG[1] = 0.;
588  TNG[2] = 0.;
589  TNG[3] = 0.;
590  TNG[4] = 0.;
591  TNG[5] = 0.;
592  }
593 
594  WorkVec.PutCoef(iFirstSubIndex + 1, -q1p + q2);
595  WorkVec.PutCoef(iFirstSubIndex + 2, -q2p - b1*b2*d*d*q1 - (b1 + b2)*d*q2 + u2);
596 }
outa_t::cd
doublereal cd
Definition: aerodc81.h:66
vam_t::density
doublereal density
Definition: aerodc81.h:108
grad::pow
GradientExpression< BinaryExpr< FuncPow, LhsExpr, RhsExpr > > pow(const GradientExpression< LhsExpr > &u, const GradientExpression< RhsExpr > &v)
Definition: gradient.h:2961
TheodorsenAeroData::alpha_pivot
doublereal * alpha_pivot
Definition: aerodata_impl.h:163
MBDYN_EXCEPT_ARGS
#define MBDYN_EXCEPT_ARGS
Definition: except.h:63
AeroData::VAM
vam_t VAM
Definition: aerodata.h:117
AeroData::GetForces
virtual int GetForces(int i, const doublereal *W, doublereal *TNG, outa_t &OUTA)
Definition: aerodata.cc:377
vam_t::bc_position
doublereal bc_position
Definition: aerodc81.h:112
TheodorsenAeroData::cfy_0
doublereal * cfy_0
Definition: aerodata_impl.h:164
TheodorsenAeroData::prev_dot_alpha
doublereal * prev_dot_alpha
Definition: aerodata_impl.h:166
TheodorsenAeroData::dot_alpha_pivot
doublereal * dot_alpha_pivot
Definition: aerodata_impl.h:163
TheodorsenAeroData::prev_time
doublereal prev_time
Definition: aerodata_impl.h:167
TheodorsenAeroData::ddot_alpha
doublereal * ddot_alpha
Definition: aerodata_impl.h:163
TheodorsenAeroData::dot_alpha
doublereal * dot_alpha
Definition: aerodata_impl.h:163
AeroMemory::GetNumPoints
int GetNumPoints(void) const
Definition: aerodata.cc:162
AeroMemory::pTime
DriveCaller * pTime
Definition: aerodata.h:67
TheodorsenAeroData::cmz_0
doublereal * cmz_0
Definition: aerodata_impl.h:164
copysign
doublereal copysign(doublereal x, doublereal y)
Definition: gradient.h:97
vam_t::force_position
doublereal force_position
Definition: aerodc81.h:111
vam_t::chord
doublereal chord
Definition: aerodc81.h:110
outa_t::cl
doublereal cl
Definition: aerodc81.h:65
TheodorsenAeroData::cfx_0
doublereal * cfx_0
Definition: aerodata_impl.h:164
TheodorsenAeroData::prev_alpha_pivot
doublereal * prev_alpha_pivot
Definition: aerodata_impl.h:166
TheodorsenAeroData::pAeroData
AeroData * pAeroData
Definition: aerodata_impl.h:169
grad::sqrt
GradientExpression< UnaryExpr< FuncSqrt, Expr > > sqrt(const GradientExpression< Expr > &u)
Definition: gradient.h:2974
VectorHandler::PutCoef
virtual void PutCoef(integer iRow, const doublereal &dCoef)=0
DriveCaller::dGet
virtual doublereal dGet(const doublereal &dVar) const =0
outa_t::clalpha
doublereal clalpha
Definition: aerodc81.h:69
TheodorsenAeroData::clalpha
doublereal * clalpha
Definition: aerodata_impl.h:165
SAFENEWARR
#define SAFENEWARR(pnt, item, sz)
Definition: mynewmem.h:701
outa_t::cm
doublereal cm
Definition: aerodc81.h:67
grad::atan2
GradientExpression< BinaryExpr< FuncAtan2, LhsExpr, RhsExpr > > atan2(const GradientExpression< LhsExpr > &u, const GradientExpression< RhsExpr > &v)
Definition: gradient.h:2962
doublereal
double doublereal
Definition: colamd.c:52
grad::tan
GradientExpression< UnaryExpr< FuncTan, Expr > > tan(const GradientExpression< Expr > &u)
Definition: gradient.h:2979
TheodorsenParams
static const doublereal TheodorsenParams[2][4]
Definition: aerodata_impl.cc:358

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DofOrder::Order TheodorsenAeroData::GetDofType ( unsigned int  i) const
virtual

Reimplemented from AeroData.

Definition at line 429 of file aerodata_impl.cc.

References DofOrder::DIFFERENTIAL.

430 {
431  return DofOrder::DIFFERENTIAL;
432 }
unsigned int TheodorsenAeroData::iGetNumDof ( void  ) const
virtual

Reimplemented from AeroData.

Definition at line 423 of file aerodata_impl.cc.

424 {
425  return 2;
426 }
std::ostream & TheodorsenAeroData::Restart ( std::ostream &  out) const
virtual

Implements AeroData.

Definition at line 395 of file aerodata_impl.cc.

References pAeroData, and AeroData::Restart().

396 {
397  out << "theodorsen";
398 
399  return pAeroData->Restart(out);
400 }
AeroData::Restart
virtual std::ostream & Restart(std::ostream &out) const =0
TheodorsenAeroData::pAeroData
AeroData * pAeroData
Definition: aerodata_impl.h:169

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void TheodorsenAeroData::SetAirData ( const doublereal &  rho,
const doublereal &  c 
)
virtual

Reimplemented from AeroData.

Definition at line 403 of file aerodata_impl.cc.

References pAeroData, and AeroData::SetAirData().

404 {
405  AeroData::SetAirData(rho, c);
406  pAeroData->SetAirData(rho, c);
407 }
AeroData::SetAirData
virtual void SetAirData(const doublereal &rho, const doublereal &c)
Definition: aerodata.cc:214
TheodorsenAeroData::pAeroData
AeroData * pAeroData
Definition: aerodata_impl.h:169
c
static std::stack< cleanup * > c
Definition: cleanup.cc:59

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void TheodorsenAeroData::SetSectionData ( const doublereal &  abscissa,
const doublereal &  chord,
const doublereal &  forcepoint,
const doublereal &  velocitypoint,
const doublereal &  twist,
const doublereal &  omega = 0. 
)
virtual

Reimplemented from AeroData.

Definition at line 410 of file aerodata_impl.cc.

References pAeroData, and AeroData::SetSectionData().

416 {
417  AeroData::SetSectionData(abscissa, chord, forcepoint, velocitypoint, twist, omega);
418  pAeroData->SetSectionData(abscissa, chord, forcepoint, velocitypoint, twist, omega);
419 }
AeroData::SetSectionData
virtual void SetSectionData(const doublereal &abscissa, const doublereal &chord, const doublereal &forcepoint, const doublereal &velocitypoint, const doublereal &twist, const doublereal &omega=0.)
Definition: aerodata.cc:237
TheodorsenAeroData::pAeroData
AeroData * pAeroData
Definition: aerodata_impl.h:169

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Member Data Documentation

doublereal TheodorsenAeroData::a
protected

Definition at line 161 of file aerodata_impl.h.

Referenced by AssJac(), and AssRes().

doublereal TheodorsenAeroData::A1
protected

Definition at line 162 of file aerodata_impl.h.

Referenced by AssJac(), and AssRes().

doublereal TheodorsenAeroData::A2
protected

Definition at line 162 of file aerodata_impl.h.

Referenced by AssJac(), and AssRes().

doublereal* TheodorsenAeroData::alpha_pivot
protected

Definition at line 163 of file aerodata_impl.h.

Referenced by AfterConvergence(), AssRes(), and ~TheodorsenAeroData().

doublereal TheodorsenAeroData::b1
protected

Definition at line 162 of file aerodata_impl.h.

Referenced by AssJac(), and AssRes().

doublereal TheodorsenAeroData::b2
protected

Definition at line 162 of file aerodata_impl.h.

Referenced by AssJac(), and AssRes().

doublereal* TheodorsenAeroData::cfx_0
protected

Definition at line 164 of file aerodata_impl.h.

Referenced by AssJac(), and AssRes().

doublereal * TheodorsenAeroData::cfy_0
protected

Definition at line 164 of file aerodata_impl.h.

Referenced by AssJac(), and AssRes().

doublereal TheodorsenAeroData::chord
protected

Definition at line 160 of file aerodata_impl.h.

Referenced by AssJac(), and AssRes().

doublereal* TheodorsenAeroData::clalpha
protected

Definition at line 165 of file aerodata_impl.h.

Referenced by AssJac(), and AssRes().

doublereal * TheodorsenAeroData::cmz_0
protected

Definition at line 164 of file aerodata_impl.h.

Referenced by AssJac(), and AssRes().

doublereal TheodorsenAeroData::d14
protected

Definition at line 159 of file aerodata_impl.h.

Referenced by AssJac(), and AssRes().

doublereal TheodorsenAeroData::d34
protected

Definition at line 159 of file aerodata_impl.h.

Referenced by AssJac(), and AssRes().

doublereal * TheodorsenAeroData::ddot_alpha
protected

Definition at line 163 of file aerodata_impl.h.

Referenced by AssJac(), and AssRes().

doublereal * TheodorsenAeroData::dot_alpha
protected

Definition at line 163 of file aerodata_impl.h.

Referenced by AfterConvergence(), AssJac(), and AssRes().

doublereal * TheodorsenAeroData::dot_alpha_pivot
protected

Definition at line 163 of file aerodata_impl.h.

Referenced by AssJac(), and AssRes().

integer TheodorsenAeroData::iParam
protected

Definition at line 158 of file aerodata_impl.h.

Referenced by AssRes().

AeroData* TheodorsenAeroData::pAeroData
protected

Definition at line 169 of file aerodata_impl.h.

Referenced by AssJac(), AssRes(), Restart(), SetAirData(), SetSectionData(), TheodorsenAeroData(), and ~TheodorsenAeroData().

doublereal* TheodorsenAeroData::prev_alpha_pivot
protected

Definition at line 166 of file aerodata_impl.h.

Referenced by AfterConvergence(), and AssRes().

doublereal * TheodorsenAeroData::prev_dot_alpha
protected

Definition at line 166 of file aerodata_impl.h.

Referenced by AfterConvergence(), and AssRes().

doublereal TheodorsenAeroData::prev_time
protected

Definition at line 167 of file aerodata_impl.h.

Referenced by AfterConvergence(), and AssRes().

The documentation for this class was generated from the following files: