Week 7 - Minor Project

AIM: To Create domain for flow analysis and Setup simulation for subsonic and supersonic regimes at different angle of attacks.

Solution procedure:

Mesh:

Method- Multizone

Face meshing

Edge sizing- 1000

Bais factor - 10000

Solver settings:

Inlet velocity: Velocity components: x-velocity = 52m/sec

y-velocity = 0

Viscous model: Default: SST kw

Solver settings:

Inlet velocity: Velocity components: x-velocity = 52m/sec

y-velocity = 0

Pseudo transient and Courant number does not have an effect in steady state analysis as in steady state analysis rate of change of variables w.r.t time is not taken into consideration.

Report definitions:

Force report: Drag >> Select 4 walls of airfoil

Force report: Lift >> Select 4 walls of airfoil

Pressure coefficients for top and bottom surface of the airfoil must be close to each other for symmetric airfoil

Expected lift for a symmetric airfoil for zero angle of attack is zero.

Expected drag for a symmetric airfoil is zero.

Inlet velocity: Velocity components: x-velocity = 52 cos(5) = 51.802m/sec

y-velocity = 52sin(5) = 4.53m/sec

Compressible flow

Everything remains the same.

Pressure based solver remains the same.

Change velocity to 272m/sec

Angle of attack 5 degree

Velocity components: x component = 272 cos(5)

y component = 272 sin (5)