Week 7 - Minor Project

AIM:

To simulate flow over an airfoil for three different Angle of Attack to find out the Lift and Drag coefficient values.

PROCEDURE TO SET UP THA CASE FOR SIMULATION:

GEOMETRY:

• Import the mesh file to fluent.
• Display all parts and check the mesh report.

TURBULENCE MODEL & MATERIALS:

• Here SST k-omega is used.
• Air is used as fluid material with constant parameters.

BOUNDARY CONDITIONS:

• Inlet as Velocity inlet with 51.21m/s.
• The outlet is considered a pressure outlet.
• For AOA 5 degree X-component flow direction is calculated as `cos(5)`.
• For AOA 5 degree Y-component flow direction is calculated as `sin(5)`.
• These steps are similar for different AOA.

SOLUTION METHOD AND REPORT DEFINITIONS:

• Coupled scheme and second-order spatial discretization method are used.
• The Courant number is reduced to 10.

• The coefficient of drag and Coefficient of lift report definition is created.

INITIALIZATION AND RUN CALCULATION:

• Standard initialization is computed from the inlet.
• For calculation 1000 iterations are set.

RESULT:

Graph of AOA Vs Cl:

Graph of AOA Vs Cd:

Graph for Aerodynamic Efficiency:

CONCLUSION:

From this simulation, we came to know how to simulate flow over an airfoil with different AOA and to calculate Cl, Cd and aerodynamic efficiency.