//==== Insert Wing Sect ====//
void WingGeom::SplitWingSect( int index )
{
WingSect* ws = GetWingSect( index );
if ( ws )
{
double span = ws->m_Span();
double rc = ws->m_RootChord();
double ac = ws->m_AvgChord();
double tc = ws->m_TipChord();
double twist = 0.5*ws->m_Twist();
int curve_type = ws->GetXSecCurve()->GetType();
string ins_id = m_XSecSurf.InsertXSec( curve_type, index );
ws->ForceSpanRcTc( span*0.5, rc, ac );
ws->m_Twist = twist;
ws->Update();
XSec* xs = m_XSecSurf.FindXSec( ins_id );
if ( xs )
{
WingSect* ins_ws = dynamic_cast< WingSect* >(xs);
ins_ws->CopyFrom( ws );
ins_ws->ForceSpanRcTc( span*0.5, ac, tc );
ins_ws->m_Twist = twist;
ins_ws->Update();
}
}
}
void WingGeom::AddDefaultSources( double base_len )
{
vector< WingSect* > ws_vec = GetWingSectVec();
double nseg = ( ( int ) ws_vec.size() ) - 1;
double ustart = 0.0;
if ( m_CapUMinOption() != VspSurf::NO_END_CAP )
{
nseg = nseg + 1.0;
ustart = ustart + 1.0;
}
if ( m_CapUMaxOption() != VspSurf::NO_END_CAP )
{
nseg = nseg + 1.0;;
}
char str[256];
LineSource* lsource;
for ( int i = 1 ; i < (int)ws_vec.size() ; i++ )
{
WingSect* ws = ws_vec[i];
if ( ws )
{
double cr = ws->m_RootChord();
double ct = ws->m_TipChord();
lsource = new LineSource();
sprintf( str, "Def_TE_LS_%d", i );
lsource->SetName( str );
lsource->m_Len = 0.01 * cr;
lsource->m_Len2 = 0.01 * ct;
lsource->m_Rad = 0.2 * cr;
lsource->m_Rad2 = 0.2 * ct;
lsource->m_ULoc1 = (i+ustart-1)/nseg;
lsource->m_WLoc1 = 0.0;
lsource->m_ULoc2 = (i+ustart)/nseg;
lsource->m_WLoc2 = 0.0;
AddCfdMeshSource( lsource );
lsource = new LineSource();
sprintf( str, "Def_LE_LS_%d", i );
lsource->SetName( str );
lsource->m_Len = 0.01 * cr;
lsource->m_Len2 = 0.01 * ct;
lsource->m_Rad = 0.2 * cr;
lsource->m_Rad2 = 0.2 * ct;
lsource->m_ULoc1 = (i+ustart-1)/nseg;
lsource->m_WLoc1 = 0.5;
lsource->m_ULoc2 = (i+ustart)/nseg;
lsource->m_WLoc2 = 0.5;
AddCfdMeshSource( lsource );
if ( i == ( ( int ) ws_vec.size() - 1 ) )
{
lsource = new LineSource();
lsource->SetName( "Def_Tip_LS" );
lsource->m_Len = 0.01 * ct;
lsource->m_Len2 = 0.01 * ct;
lsource->m_Rad = 0.2 * ct;
lsource->m_Rad2 = 0.2 * ct;
lsource->m_ULoc1 = (i+ustart)/nseg;
lsource->m_WLoc1 = 0.0;
lsource->m_ULoc2 = (i+ustart)/nseg;
lsource->m_WLoc2 = 0.5;
AddCfdMeshSource( lsource );
}
}
}
}
//==== 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();
}
