//==== Constructor ====//
WingGeom::WingGeom( Vehicle* vehicle_ptr ) : GeomXSec( vehicle_ptr )
{
m_Name = "WingGeom";
m_Type.m_Name = "Wing";
m_Type.m_Type = MS_WING_GEOM_TYPE;
m_MinActiveXSec = 1;
m_Closed = false;
m_XSecSurf.SetParentContainer( GetID() );
m_XSecSurf.SetBasicOrientation( vsp::Y_DIR, X_DIR, XS_SHIFT_LE, true );
m_RelativeDihedralFlag.Init("RelativeDihedralFlag", m_Name, this, 0, 0, 1, true );
m_RelativeDihedralFlag.SetDescript( "Relative or Absolute Dihedral" );
m_RelativeTwistFlag.Init("RelativeTwistFlag", m_Name, this, 0, 0, 1, true );
m_RelativeTwistFlag.SetDescript( "Relative or Absolute Twist" );
m_RotateAirfoilMatchDiedralFlag.Init("RotateAirfoilMatchDideralFlag", m_Name, this, 0, 0, 1, true );
m_RotateAirfoilMatchDiedralFlag.SetDescript( "Rotate Airfoil To Stay Tangent To Dihedral (or Not)" );
m_TotalSpan.Init( "TotalSpan", m_Name, this, 1.0, 1e-6, 1000000.0 );
m_TotalSpan.SetDescript( "Total Planform Span" );
m_TotalProjSpan.Init( "TotalProjectedSpan", m_Name, this, 1.0, 1e-6, 1000000.0 );
m_TotalProjSpan.SetDescript( "Total Projected Planform Span" );
m_TotalChord.Init( "TotalChord", m_Name, this, 1.0, 0.0, 1000000.0 );
m_TotalChord.SetDescript( "Total Planform Chord" );
m_TotalArea.Init( "TotalArea", m_Name, this, 1.0, 1e-10, 1.0e12 );
m_TotalArea.SetDescript( "Total Planform Area" );
//==== rename capping controls for wing specific terminology ====//
m_CapUMinOption.SetDescript("Type of End Cap on Wing Root");
m_CapUMinOption.Parm::Set(VspSurf::FLAT_END_CAP);
m_CapUMinTess.SetDescript("Number of tessellated curves on Wing Root");
m_CapUMaxOption.SetDescript("Type of End Cap on Wing Tip");
m_CapUMaxOption.Parm::Set(VspSurf::FLAT_END_CAP);
m_CapUMaxTess.SetDescript("Number of tessellated curves on Wing Tip");
//==== Init Parms ====//
m_TessU = 16;
m_TessW = 31;
m_ActiveXSec = 1;
m_ActiveAirfoil = 0;
m_SymPlanFlag = SYM_XZ;
//==== Wing XSecs ====//
m_XSecSurf.SetXSecType( XSEC_WING );
m_XSecSurf.SetCutMinNumXSecs( 2 );
m_XSecSurf.AddXSec( vsp::XS_FOUR_SERIES );
m_XSecSurf.AddXSec( vsp::XS_FOUR_SERIES );
WingSect* ws;
ws = ( WingSect* ) m_XSecSurf.FindXSec( 0 );
ws->SetGroupDisplaySuffix( 0 );
ws = ( WingSect* ) m_XSecSurf.FindXSec( 1 );
ws->SetGroupDisplaySuffix( 1 );
ws->m_Sweep = 30.0;
ws->m_RootChord = 4.0;
ws->m_TipChord = 1.0;
ws->m_Span = 9.0;
UpdateSurf();
}
//==== Update Wing And Cross Section Placement ====//
void WingGeom::UpdateSurf()
{
//==== Check If Total Span/Chord/Area Has Changed ====//
bool total_change_flag = false;
if ( UpdatedParm( m_TotalSpan.GetID() ) )
{
UpdateTotalSpan();
total_change_flag = true;
}
if ( UpdatedParm( m_TotalProjSpan.GetID() ) )
{
UpdateTotalProjSpan();
total_change_flag = true;
}
if ( UpdatedParm( m_TotalChord.GetID() ) )
{
UpdateTotalChord();
total_change_flag = true;
}
if ( UpdatedParm( m_TotalArea.GetID() ) )
{
UpdateTotalArea();
total_change_flag = true;
}
int active_sect = GetActiveXSecIndex(); // Save Active Section
//==== Set Temp Active XSec Based On Updated Parms ====//
if ( total_change_flag )
SetActiveXSecIndex(1);
else
SetTempActiveXSec();
//==== Make Sure Chord Match For Adjacent Wing Sections ====//
MatchWingSections();
SetActiveXSecIndex(active_sect); // Restore Active Section
// clear the u tessellation vector
m_TessUVec.clear();
vector< VspCurve > crv_vec( m_XSecSurf.NumXSec() );
//==== Compute Parameters For Each Section ====//
double total_span = 0.0;
double total_sweep_offset = 0.0;
double total_dihed_offset = 0.0;
double total_twist = 0.0;
//==== Load End Points for Each Section ====//
for ( int i = 0 ; i < m_XSecSurf.NumXSec() ; i++ )
{
WingSect* ws = ( WingSect* ) m_XSecSurf.FindXSec( i );
if ( ws )
{
//==== Reset Group Names ====//
ws->SetGroupDisplaySuffix( i );
double rad = ws->m_Span();
double ty = rad*cos(GetSumDihedral(i)*DEG_2_RAD);
double tz = rad*sin(GetSumDihedral(i)*DEG_2_RAD);
double tan_le = ws->GetTanSweepAt( ws->m_Sweep(), 0.0 );
double toff = tan_le*rad; // Tip X Offset
if ( i == 0 )
{
ty = 0;
tz = 0;
toff = 0;
}
total_dihed_offset += tz;
total_span += ty;
total_sweep_offset += toff;
if ( m_RelativeTwistFlag() )
total_twist += ws->m_Twist();
else
total_twist = ws->m_Twist();
ws->SetProjectedSpan( ty );
//==== Find Width Parm ====//
string width_id = ws->GetXSecCurve()->GetWidthParmID();
Parm* width_parm = ParmMgr.FindParm( width_id );
if ( width_parm )
{
width_parm->Deactivate();
width_parm->Set( ws->m_TipChord() );
}
double dihead_rot = 0.0;
if ( m_RotateAirfoilMatchDiedralFlag() )
{
if ( i == 0 )
{
dihead_rot = GetSumDihedral( i+1 );
}
else if ( i == m_XSecSurf.NumXSec()-1 )
{
dihead_rot = GetSumDihedral( i );
}
else
{
dihead_rot = 0.5*( GetSumDihedral( i ) + GetSumDihedral( i+1 ) );
}
}
//==== Load Transformations =====//
ws->m_YDelta = total_span;
ws->m_XDelta = total_sweep_offset;
ws->m_ZDelta = total_dihed_offset;
ws->m_YRotate = total_twist;
ws->m_XRotate = dihead_rot;
ws->m_XCenterRot = ws->m_XDelta + ws->m_TwistLoc()*ws->m_TipChord();
ws->m_YCenterRot = ws->m_YDelta;
ws->m_ZCenterRot = ws->m_ZDelta;
crv_vec[i] = ws->GetCurve();
if ( i > 0 )
{
m_TessUVec.push_back( ws->m_SectTessU() );
}
}
}
m_MainSurfVec[0].SkinC0( crv_vec, false );
if ( m_XSecSurf.GetFlipUD() )
{
m_MainSurfVec[0].FlipNormal();
}
m_MainSurfVec[0].SetSurfType( vsp::WING_SURF );
//==== Load Totals ====//
m_TotalSpan = ComputeTotalSpan();
m_TotalProjSpan = ComputeTotalProjSpan();
m_TotalChord = ComputeTotalChord();
m_TotalArea = ComputeTotalArea();
}
