NACA0012 Airfoil Optimization With RBF Morph, CFD Simulation Ansys Fluent Training
$315.00 Student Discount
In this project, a NACA0012 Airfoil with the RBF (Mesh Morphing) Method has been simulated, and the results of this simulation have been investigated.
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Description
NACA0012 Airfoil Optimization Project Description
In this project, the flow inside a NACA0012 airfoil is first has been simulated by Ansys Fluent software. The angle of attack is 1.53 degrees, and the simulation has been done by the densitybased solver due to the compressibility with a Mach number equal to 0.7. Then the geometry is optimized to improve lifttodrag (L/D)Â as aerodynamic efficiency. All the optimization has been done by Ansys Fluent software in the Ansys Workbench environment.
The optimization step is performed in three stages. In the first stage, only the displacement of points in the vertical direction was considered, and the best answers were obtained for the maximum lifttodrag ratio and maximum lift coefficient. Then in the next step, each of these two optimal solutions was considered for horizontal displacement, and the lifttodrag ratio was obtained in two new modes.
For this purpose, an area is defined around the airfoil, the center of which is (0,0.5), with the regular control point distribution. The update from the zone is set for the airfoil walls, and this wall’s constraint type is set to unconstrained type. The length and the height of this rectangle are 1 meter. The number of nodes in the Xdirection is 12, and the number of nodes in the Ydirection is 4. In fact, the input parameter for this optimization is the vertical and horizontal displacement of these points.
The constraint for another boundary (Farfield) is set to fix. To begin the optimization process, you have to define the motion for each of these points. In this project, for points numbers, 28,29, and 30, the displacement to the +y is considered, and for point 27, the displacement to both x and +y directions is considered. In the first stage, no horizontal displacement is considered, and the optimal result is obtained only based on vertical displacement. Then, in the next step, based on the best answer of the lift and drag ratio, the amount of vertical displacement is selected. Horizontal displacement is then applied and optimized for vertical displacement to obtain the best lifttodrag ratio. This optimization has been done once for the best lift coefficient. Finally, the results are compared.
Geometry & Mesh
The geometry is designed by the Design Modeler Software, and the meshing of this model has been generated by Ansys Meshing software. The grid type is structured and the total cell number is 73320.
NACA0012 Airfoil CFD Simulation
To simulate the present model, several assumptions are considered, which are:
 The solver is densitybased due to compressibility.
 Simulation has been done as steadystate.
 The gravity effect has been neglected.
The following is a summary of the steps for defining the problem and its solution:
Models  
Viscous  Spalart Allmaras  
Spalart Allmaras Production  Strain/Vorticitybased  
Boundary conditions  
Farfield  Mach Number  
Pressure Fairfield  0.7
Xcomponent of flow direction: 0.9996435 Ycomponent of flow direction: 0.02670036 

Airfoil Up & Airfoil Bottom  Wall  
Wall motion  Stationary Wall  
Shear Condition  Noslip condition  
Methods  
Formulation
Flux type 
Implicit
RoeFDS 

Flow & Modified turbulent viscosity  Secondorder upwind  
gradient  Green Gauss Nodebased  
Initialization  
Initialization methods  Standard  
Compute from  Farfield  
Material  
Material properties  
density  Ideal gas  
viscosity  Sutherland  
Cp  1006.43 
NACA0012 Airfoil Optimization Results
First Step Optimization
In the second case, the shock is observed on the upper surface of the airfoil, which is almost a normal shock. As it is known, after this shock, the flow velocity has suddenly decreased, which has intensified the separation in this area. On the other hand, due to the concavity created in the lower surface of the airfoil, the difference between the forces of the upper and lower levels of the airfoil has caused a negative lift.
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