Week 7 - Minor Project
Aim
To create domain for flow analysis and analyse at 3 different angles of attack and the lift and drag coefficient.
3D cad model
Mesh
Mesh size 40 mm
Boundary Conditions
Models used
Solver - Pressure based
Velocity formulation - Absolute
Time - Steady
2D space - Plannar
Viscous - k-Omega - SST
Properties of air taken for 15000 feet
Boundary conditions
Inlet - Velocity Inlet
Outlet - Pressure Outlet
Farfeild - Symmetry
Results
Incompressible flow
AOA = 5
Velocity Contour
Static pressure contour
Dynamic pressure contour
AOA = 10
Velocity Contour
Static pressure contour
Dynamic pressure contour
AOA = 15
Velocity Contour
Static pressure contour
Dynamic pressure contour
Compressible Flow
AOA = 5
Velocity Contour
Static pressure contour
Dynamic pressure contour
AOA = 10
Velocity Contour
Static pressure contour
Dynamic pressure contour
AOA = 15
Velocity Contour
Static pressure contour
Dynamic pressure contour
Conclusion
For the incompressible flow as the AOA is increased the Cl and Cd increases but for compressible flow 15 deg AOA is decreased because it is near the stalling condition. If you compare the AOA of the incompressible and compressible flow the Cl and Cd is more for compressible flow because of the velocity, as the velocity increases the lift increases.