From fd0b511de038918c8e52e059a3cec19e25df16b3 Mon Sep 17 00:00:00 2001
From: michael <michael@localhost.localdomain>
Date: Sun, 29 Nov 2020 00:12:52 +0100
Subject: [PATCH] Added simulation of NACA airfoil

---
 CoreFlows/examples/Python/CMakeLists.txt      |  1 +
 .../SinglePhase/SinglePhase_2DAirfoil.py      | 99 +++++++++++++++++++
 2 files changed, 100 insertions(+)
 create mode 100644 CoreFlows/examples/Python/SinglePhase/SinglePhase_2DAirfoil.py

diff --git a/CoreFlows/examples/Python/CMakeLists.txt b/CoreFlows/examples/Python/CMakeLists.txt
index 7fe76f6..f24f688 100755
--- a/CoreFlows/examples/Python/CMakeLists.txt
+++ b/CoreFlows/examples/Python/CMakeLists.txt
@@ -125,6 +125,7 @@ CreatePythonTest(SinglePhase/SinglePhase_2DLidDrivenCavity_unstructured.py)
 CreatePythonTest(SinglePhase/SinglePhase_2DPoiseuilleFlow.py)
 CreatePythonTest(SinglePhase/SinglePhase_2DPoiseuilleFlow_restart.py)
 CreatePythonTest(SinglePhase/SinglePhase_2DPoiseuilleFlow_outputFields.py)
+CreatePythonTest(SinglePhase/SinglePhase_2DAirfoil.py)
 CreatePythonTest(SinglePhase/SinglePhase_2DSphericalExplosion_unstructured.py)
 CreatePythonTest(SinglePhase/SinglePhase_2DSphericalExplosion_HEXAGON.py)
 CreatePythonTest(SinglePhase/SinglePhase_2DHeatedChannelInclined.py)
diff --git a/CoreFlows/examples/Python/SinglePhase/SinglePhase_2DAirfoil.py b/CoreFlows/examples/Python/SinglePhase/SinglePhase_2DAirfoil.py
new file mode 100644
index 0000000..3ad0def
--- /dev/null
+++ b/CoreFlows/examples/Python/SinglePhase/SinglePhase_2DAirfoil.py
@@ -0,0 +1,99 @@
+#!/usr/bin/env python3
+# -*-coding:utf-8 -*
+
+import CoreFlows as cf
+import cdmath as cm
+
+def SinglePhase_2DAirfoil():
+	spaceDim = 2;
+
+    # Prepare the mesh data
+	print("Loading the mesh" );
+	filename="./resources/naca10.med"
+	my_mesh=cm.Mesh(filename)
+       
+	# Boundary data
+	inletVelocityX   = 175;
+	inletVelocityY   = 0.;
+	inletTemperature = 300
+	outletPressure   = 1e5
+	wallVelocityX    = 0;
+	wallVelocityY    = 0;
+	wallTemperature  = 300;
+
+    # physical constants
+	gravite  = [0] * spaceDim
+	gravite[0]= 0;
+	gravite[1]= -10;
+	viscosity = 15e-6
+	viscosite = [viscosity];
+
+	myProblem = cf.SinglePhase(cf.Gas,cf.around1bar300K,spaceDim);
+	nVar =myProblem.getNumberOfVariables();
+
+    # Prepare for the initial condition
+	VV_Constant =[0]*nVar
+
+	VV_Constant[0] = outletPressure ;
+	VV_Constant[1] = inletVelocityX;
+	VV_Constant[2] = inletVelocityY;
+	VV_Constant[3] = inletTemperature ;
+
+    #Initial field creation
+	print("Setting initial data" );
+	myProblem.setInitialFieldConstant(my_mesh,VV_Constant)
+
+    # the boundary conditions
+	myProblem.setOutletBoundaryCondition("Inlet", outletPressure);
+	myProblem.setInletBoundaryCondition( "Outlet", inletTemperature, inletVelocityX, inletVelocityY);
+	myProblem.setWallBoundaryCondition("Top",     wallTemperature, wallVelocityX, wallVelocityY);
+	myProblem.setWallBoundaryCondition("Bottom",  wallTemperature, wallVelocityX, wallVelocityY);
+	myProblem.setWallBoundaryCondition("Airfoil_boundary", wallTemperature, wallVelocityX, wallVelocityY);
+
+    # set physical parameters
+	myProblem.setViscosity(viscosite);
+	myProblem.setGravity(gravite);
+
+	# set the numerical method
+	myProblem.setNumericalScheme(cf.upwind, cf.Implicit);
+	myProblem.setLinearSolver(cf.GMRES,cf.ILU,True);
+    
+	# name file save
+	fileName = "2DAirfoil";
+
+	# parameters calculation
+	MaxNbOfTimeStep = 10000 ;
+	freqSave = 100;
+	cfl = 50;
+	maxTime = 5000;
+	precision = 1e-4;
+
+	myProblem.setCFL(cfl);
+	myProblem.setPrecision(precision);
+	myProblem.setMaxNbOfTimeStep(MaxNbOfTimeStep);
+	myProblem.setTimeMax(maxTime);
+	myProblem.setNewtonSolver(precision,50);
+	myProblem.setFreqSave(freqSave);
+	myProblem.setFileName(fileName);
+	if(spaceDim>1):
+		myProblem.saveVelocity();
+		pass
+
+	# evolution
+	myProblem.initialize();
+
+	ok = myProblem.run();
+	if (ok):
+		print( "Simulation " + fileName + " is successful !" );
+		pass
+	else:
+		print( "Simulation " + fileName + "  failed ! " );
+		pass
+
+	print( "------------ End of Simulation !!! -----------" );
+
+	myProblem.terminate();
+	return ok
+
+if __name__ == """__main__""":
+    SinglePhase_2DAirfoil()
-- 
2.39.2