Flap Effect on Trailing Edge of an Airfoil, CFD Simulation
In this project, steady airflow over a flapped airfoil with an attack angle equal to 12 degrees is investigated.
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Airfoil with a Flap Problem description
In this project, steady airflow over a flapped airfoil with an attack angle equal to 12 degrees is investigated. Air velocity magnitude is equal to 45 m/s. The lift coefficient of an airfoil with and without the flap is equal to 1.2182 and 1.0530, which shows the effectiveness of flap in aerodynamic lift force generation. Moreover, the drag coefficient of the airfoil in the presence of flap is equal to -0.0273, which is less than airfoil without flap where the drag coefficient is equal to -0.0822, which proves that flap presence is effective in drag force reduction that is favorable in aerodynamics applications.
Flap Geometry and mesh
The fluid domain’s geometry is designed in the Design Modeler, and the computational grid is generated using Ansys meshing. The mesh type is unstructured, and the element number is 64731.
- The solver type is assumed Pressure Based.
- Time formulation is assumed Steady.
- The gravity effect is neglected.
The following table presents a summary of the defining steps of the problem and its solution.
|Fluid||Definition method||Fluent Database|
|X velocity||44.015999 m/s|
|Y velocity||9.3559999 m/s|
|Turbulent kinetic energy||1 m2/s2|
|Specific dissipation rate||1|
|Spatial discretization||Gradient||Least square cell-based|
|Momentum||Second order Upwind|
|K||First order Upwind|
|Epsilon||First order Upwind|
Results and discussion
Air mass flow rate at outlet is equal to -1193.004 kg/s. Drag and lift force for flapped airfoil is equal to 36.420259 and 1526.8363 N.
There are a Mesh file and a comprehensive Training Movie that presents how to solve the problem and extract all desired results.