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meshGFaceExtruded.cpp
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Christophe Geuzaine authoredChristophe Geuzaine authored
magnus.pro 13.19 KiB
/* -------------------------------------------------------------------
Tutorial 6 : Potential flow, lift and Magnus effect
Features:
- Potential flow, irrotational flow, lift and Magnus effect
- Multivalued scalar field
- Non-linear iteration on an Associated global quantity
- Use a run-time variable in a Post-Operation
To compute the solution in a terminal:
getdp magnus.pro -solve PotentialFlow -pos PotentialFlow
gmsh magnus.geo velocity.pos
To compute the solution interactively from the Gmsh GUI:
File > Open > magnus.pro
Run (button at the bottom of the left panel)
------------------------------------------------------------------- */
/*
This model solves a 2D potential flow around a cylinder or a naca airfoil
placed in a uniform "V_infinity" flow.
Potential flows are defined by
V = grad phi => curl V = 0
where the multivalued scalar potential "phi"
presents a discontinuity of magnitude "deltaPhi"
across a cut "Sur_Cut".
In consequence, the velocity field "V" is curl-free
over the wole domain of analysis "Vol_rho"
but its circulation over any closed curve circling around the object,
a quantity often noted "Gamma" in the literature,
gives "deltaPhi" as a result.
The circulation of "V" over closed curves
not circling around the object is zero.
In the getDP model, the discontinuity "deltaPhi" [m^2/s]
is defined as a global quantity in the Functional space of "phi".
The associated (dual) global quantity is the mass flow density,
noted "Dmdt", which has [kg/s] as a unit.
Governing equations are
div ( rho[] grad phi ) = 0 in Vol_rho
rho[] grad phi . n = rho[] Vn = 0 on Sur_Neu
whereas the uniform velocity field "V_infinity" is imposed
by means of Dirichlet boundary conditions
on the upstream and downstream surfaces "GammaUp" and "GammaDown".
Momentum equation is decoupled in case of stationary potential flows.
The velocity filed can be solved first, and the pressure
is obtained afterwards by invoking Bernoulli's theorem:
p = -0.5 * rho[] * SquNorm [ {d phi} ]
The "Lift" force in "Y" direction is then evaluated
either by integrating "p * CompY[Normal[]]"
over the contour of the object,
or by the Kutta-Jukowski theorem
Lift = - L_z rho[] V_infinity Gamma
which is a first order approximation of the former.
"Cylinder" case:
Either the circulation "deltaPhi" or the mass flow rate "Dmdt"
can be imposed, according to the "Flag_Circ" flag.
The Lift is evaluated by both the integration of pressure
and the Kutta-Jukowski approximation.
"Airfoil" case:
If "Flag_Circ == 1", the model works similar to the "Cylinder" case.
If "Flag_Circ == 0", the mass flow rate is not directly imposed
in this case.
It is determined so that the Kutta condition is verified.
This condition states that the actual value of "Dmdt"
is the one for which the stagnation point
(singularity of the velocity field)
is located at the trailing edge of the airfoil,.
This is true when the function
argVTrail[] = ( Atan2[CompY[$1], CompX[$1] ] - Incidence ) / deg ;
returns zero when evaluated for the velocity at a point "P_edge"
close to the trailing edge of the airfoil.
A non linear iteration is thus done by means of a pseudo-newton scheme,
updating the value of the imposed "Dmdt" until the norm of the residual
f(V) = argVTrail[ {d phi } ] OnPoint {1.0001,0,0}
comes below a fixed tolerance.
*/
Include "magnus_common.pro";
Group{
// Physical regions
Fluid = Region[ 2 ];
GammaUp = Region[ 10 ];
GammaDown = Region[ 11 ];
GammaAirf = Region[ 12 ];
GammaCut = Region[ 13 ];
// Abstract regions
Vol_rho = Region[ { Fluid } ];
Sur_Dir = Region[ { GammaUp, GammaDown } ];
Sur_Neu = Region[ { GammaAirf } ];
Sur_Cut = Region[ { GammaCut } ];
}
Function{
rho[] = 1.225; // kg/m^3
MassFlowRate[] = MassFlowRate; // kg/s
DeltaPhi[] = DeltaPhi; // m^2/s
argVTrail[] = ( Atan2[CompY[$1], CompX[$1] ] - Incidence ) / deg ;
}
Jacobian {
{ Name Vol ;
Case {
{ Region All ; Jacobian Vol ; }
}
}
{ Name Sur ;
Case {
{ Region All ; Jacobian Sur ; }
}
}
}
Integration {
{ Name Int ;
Case {
{ Type Gauss ;
Case {
{ GeoElement Point ; NumberOfPoints 1 ; }
{ GeoElement Line ; NumberOfPoints 4 ; }
{ GeoElement Triangle ; NumberOfPoints 6 ; } { GeoElement Quadrangle ; NumberOfPoints 7 ; }
{ GeoElement Tetrahedron ; NumberOfPoints 15 ; }
{ GeoElement Hexahedron ; NumberOfPoints 34 ; }
}
}
}
}
}
Constraint{
{ Name Dirichlet; Type Assign;
Case{
// Boundary conditions for the V_infinity uniform flow
{ Region GammaDown; Value Velocity*BoxSize; }
{ Region GammaUp ; Value 0; }
}
}
{ Name DeltaPhi; Type Assign;
Case{
{ Region Sur_Cut; Value DeltaPhi[]; }
}
}
{ Name MassFlowRate; Type Assign;
Case{
{ Region Sur_Cut; Value MassFlowRate[]; }
}
}
}
// Domains of definition used in the description of the function space
// These groups contain both volume and surface regions/elements.
Group{
Dom_Vh = Region[ { Vol_rho, Sur_Dir, Sur_Neu, Sur_Cut } ];
Dom_Cut = ElementsOf[ Dom_Vh, OnPositiveSideOf Sur_Cut ];
}
FunctionSpace{
{ Name Vh; Type Form0;
BasisFunction{
{ Name vn; NameOfCoef phin; Function BF_Node;
Support Dom_Vh; Entity NodesOf[All]; }
{ Name vc; NameOfCoef dphi; Function BF_GroupOfNodes;
Support Dom_Cut; Entity GroupsOfNodesOf[ Sur_Cut ];}
}
SubSpace {
{ Name phiCont ; NameOfBasisFunction { vn } ; }
{ Name phiDisc ; NameOfBasisFunction { vc } ; }
}
GlobalQuantity {
{ Name Circ ; Type AliasOf ; NameOfCoef dphi ; }
{ Name Dmdt ; Type AssociatedWith ; NameOfCoef dphi ; }
}
Constraint{
{NameOfCoef phin; EntityType NodesOf;
NameOfConstraint Dirichlet;}
If( Flag_Circ )
{NameOfCoef Circ; EntityType GroupsOfNodesOf;
NameOfConstraint DeltaPhi;}
Else
If( Flag_Object == 0 ) // if Cylinder only
// In case of the Airfoil, the contraint on Dmdt is omitted
// and replaced by an equation "Dmdt=$newDmdt"
// See the "Resolution" section.
{NameOfCoef Dmdt; EntityType GroupsOfNodesOf;
NameOfConstraint MassFlowRate;}
EndIf
EndIf
}
}
}
Formulation{
{Name PotentialFlow; Type FemEquation;
Quantity{
{Name phi; Type Local; NameOfSpace Vh;}
{ Name phiCont ; Type Local ; NameOfSpace Vh[phiCont] ; }
{ Name phiDisc ; Type Local ; NameOfSpace Vh[phiDisc] ; }
{ Name Circ ; Type Global ; NameOfSpace Vh[Circ] ; }
{ Name Dmdt ; Type Global ; NameOfSpace Vh[Dmdt] ; }
}
Equation{
Galerkin{[ rho[] * Dof{d phi}, {d phi}];
In Vol_rho; Jacobian Vol; Integration Int;}
If( !Flag_Circ )
GlobalTerm { [ -Dof{Dmdt} , {Circ} ] ; In Sur_Cut ; }
If( Flag_Object == 1 )
GlobalTerm { [ -Dof{Dmdt} , {Dmdt} ] ; In Sur_Cut ; }
GlobalTerm { [ $newDmdt , {Dmdt} ] ; In Sur_Cut ; }
EndIf
EndIf
}
}
}
Resolution{
{Name PotentialFlow;
System{
{Name A; NameOfFormulation PotentialFlow;}
}
Operation{
InitSolution[A];
If( Flag_Circ || ( Flag_Object == 0 ) )
Generate[A]; Solve[A]; SaveSolution[A];
Else
// Pseudo-Newton iteration to determine Dmdt in the Airfoil case.
// The run-time variable $newDmdt is used in Generate[A]
// whereas $circ, $dmdt, $argV and $phiTrailing are evaluated
// by the PostOperation[Trailing].
// A file containing "PhiTrailing = $phiTrailing;" is after all
// written on disk to be used for formatting the
DeleteFile["KJiter.txt"];
Evaluate[$newDmdt = MassFlowRate];
Evaluate[ $syscount = 0 ];
Generate[A]; Solve[A]; SaveSolution[A];
Evaluate[$dmdtp = MassFlowRate];
Evaluate[$argVp = DeltaPhi];
PostOperation[Trailing];
Print[{$syscount, $circ, $dmdt, $argV},
Format "iter = %3g Circ = %5.2f Dmdt = %5.2f argV = %5.2e"];
While[ Norm[ $argV ] > 1e-3 && $syscount < 50] {
Test[ $syscount && Norm[$argV-$argVp] > 1e-3 ]
{Evaluate[$jac = Min[ ($dmdt-$dmdtp)/($argV-$argVp), 0.2 ] ] ;}
{Evaluate[$jac = 0.2];}
Print[{$jac}, Format "Jac = %7.5e"];
Evaluate[$newDmdt = $dmdt - $jac * $argV];
Evaluate[ $syscount = $syscount + 1 ];
Generate[A]; Solve[A]; SaveSolution[A];
Evaluate[$dmdtp = $dmdt];
Evaluate[$argVp = $argV];
PostOperation[Trailing];
Print[{$syscount, $circ, $dmdt, $jac, $argV},
Format "iter = %3g Circ = %5.2f Dmdt = %5.2f jac=%5.2f argV = %5.3e"];
}
Print[{$phiTrailing}, Format "PhiTrailing=%g;", File "PhiTrailing.txt"];
EndIf
}
}
}
PostProcessing{
{Name PotentialFlow; NameOfFormulation PotentialFlow;
Quantity{
{Name phi; Value {
Local{ [ {phi} ] ; In Dom_Vh; Jacobian Vol; } } }
{ Name phiCont ; Value {
Local { [ { phiCont } ] ; In Dom_Vh ; Jacobian Vol ; } } }
{ Name phiDisc ; Value {
Local { [ { phiDisc } ] ; In Dom_Vh ; Jacobian Vol ; } } }
{Name velocity; Value {
Local { [ {d phi} ]; In Dom_Vh; Jacobian Vol; } } }
{Name normVelocity; Value {
Local { [ Norm[{d phi}] ]; In Dom_Vh; Jacobian Vol; } } }
{Name pressure; Value {
Local { [-0.5*rho[]*SquNorm[ {d phi} ]];
In Dom_Vh; Jacobian Vol; } } }
{Name Angle; Value {
Local{ [ argVTrail[{d phi}] ];
In Dom_Vh; Jacobian Vol; } } }
{ Name Circ; Value { Local { [ {Circ} ]; In Sur_Cut; } } }
{ Name Dmdt; Value { Local { [ {Dmdt} ]; In Sur_Cut; } } }
// Kutta-Jukowski approximation for Lift
{ Name LiftKJ; Value { Local { [ -rho[]*{Circ}*Velocity ];
In Sur_Cut; } } }
// Lift computed with the real pressure field
{ Name Lift;
Value {
Integral { [ -0.5*rho[]*SquNorm[{d phi}]*CompY[Normal[]] ];
In Dom_Vh ; Jacobian Sur ; Integration Int; }
}
}
{ Name circulation;
Value {
Integral { [ {d phi} * Tangent[] ] ;
In Dom_Vh ; Jacobian Sur ; Integration Int; }
}
}
}
}
}
PostOperation{
{Name PotentialFlow; NameOfPostProcessing PotentialFlow;
Operation{
Print[Circ, OnRegion Sur_Cut, File > "output.txt", Color "Ivory",
Format Table, SendToServer "Output/Circ" ];
Print[Dmdt, OnRegion Sur_Cut, File > "output.txt", Color "Ivory",
Format Table, SendToServer "Output/Dmdt" ];
Print[LiftKJ, OnRegion Sur_Cut, File > "output.txt", Color "Ivory",
Format Table, SendToServer "Output/LiftKJ" ];
Print[Lift[GammaAirf], OnGlobal, Format Table,
File > "output.txt", Color "Ivory",
SendToServer "Output/Lift"];
// Uncomment these lines to have more color maps
//Print[phi, OnElementsOf Vol_rho, File "phi.pos"];
//Print[phiDisc, OnElementsOf Vol_rho, File "phiDisc.pos"];
//Print[phiCont, OnElementsOf Vol_rho, File "phiCont.pos"];
//Print[pressure, OnElementsOf Vol_rho, File "p.pos"];
Print[ velocity, OnElementsOf Vol_rho, File "velocity.pos"];
Echo[ Str["l=PostProcessing.NbViews-1;",
"View[l].VectorType = 1;",
"View[l].LineWidth = 2;",
"View[l].ArrowSizeMax = 100;",
"View[l].CenterGlyphs = 1;"],
File "tmp.geo", LastTimeStepOnly] ;
// Stagnation points are points where Norm[{d phi}] is zero
// This is better seen in log scale.
Print[normVelocity, OnElementsOf Vol_rho, File "p.pos"];
Echo[ Str["l=PostProcessing.NbViews-1;",
"View[l].Name = 'stagnation points';",
"View[l].ScaleType = 2;"],
File "tmp.geo", LastTimeStepOnly] ;
// Show the isovalue phi=$PhiTrailing
// which should be perpendicular to the airfoil
// if the Kutta condition is fulfilled
Print[phi, OnElementsOf Vol_rho, File "KJ.pos"];
Echo[Str["Merge 'PhiTrailing.txt';",
"l=PostProcessing.NbViews-1;",
"View[l].Name = 'isovalue phiTrailing';",
"View[l].IntervalsType = 3;",
"Mesh.SurfaceEdges = 0;",
"View[l].RangeType = 2;",
"View[l].CustomMin = PhiTrailing;",
"View[l].CustomMax = 1.001*PhiTrailing;",
"View[l].NbIso = 10;"],
File "tmp.geo", LastTimeStepOnly] ;
}
}
}
PostOperation{ // for the Airfoil model
{Name Trailing; NameOfPostProcessing PotentialFlow;
Operation{
Print[Circ, OnRegion Sur_Cut, File > "KJiter.txt", Format Table,
StoreInVariable $circ,
SendToServer "Output/Circ" ];
Print[Dmdt, OnRegion Sur_Cut, File > "KJiter.txt", Format Table,
StoreInVariable $dmdt,
SendToServer "Output/Dmdt" ];
Print[phi, OnPoint{1.0001,0,0}, File > "KJiter.txt", Color "Ivory",
StoreInVariable $phiTrailing,
Format Table, SendToServer "Output/PhiTrailing"];
Print[Angle, OnPoint{1.0001,0,0}, File > "KJiter.txt", Color "Ivory",
StoreInVariable $argV,
Format Table, SendToServer "Output/argVTrailing"];
}
}
}
DefineConstant[
R_ = {"PotentialFlow", Name "GetDP/1ResolutionChoices", Visible 0},
C_ = {"-solve -pos", Name "GetDP/9ComputeCommand", Visible 0},
P_ = {"PotentialFlow", Name "GetDP/2PostOperationChoices", Visible 0}
];