## Engineering

This Analysis presents a downwash detection and localization strategy intended for use on  rotorcrafts. A downwash and its effect is analysed due to the rotory motion of the Helicopter's rotor operating at sea level, it is assumed that the rotor is moving at 3500 RPM. The NACA23013 airfoil is used for the rotors.

Geometry:

Geometry with enclosure:

Meshing:

Boundary Condition:

• Inlet-Pressure-Atmospheric
• Outlet-Outflow
• Outer boundary-Wall
• Rotor-wall
• Fuselage-wall

Geometry for SRF Models:

Domain boundaries typically consist of:

• Inlets and outlets
• Walls
• Periodic boundaries (rotational refrence Frame (SRF).

SRF Models:

• Many problems permit the entire computational domain to be referred to a single moving reference frame (hence the name SRF modeling). In such cases, the equations given in Equations for a Moving Reference Frame are solved in all fluid cell zones. Steady-state solutions are possible in SRF models provided suitable boundary conditions are prescribed. In particular, wall boundaries must adhere to the following requirements:
• Any walls that are moving with the reference frame can assume any shape. An example would be the blade surfaces associated with a pump impeller. The no slip condition is defined in the relative frame such that the relative velocity is zero on the moving walls.
• For a rotating problem, you can define walls that are non-moving with respect to the stationary coordinate system, but these walls must be surfaces of revolution about the axis of rotation. Here the no slip condition is defined such that the absolute velocity is zero on the walls. An example of this type of boundary would be a cylindrical wind tunnel wall that surrounds a rotating propeller.

Results:-

Pressure contour at .5 m above rotor:

Velocity Vector  at .5 m above rotor:

Velocity Vector  at .5 m above rotor:

Pressure contour at Rotor:

Velocity contour at rotor:

Pressure contour just below the Fuselage:

Velocity contour just below the Fuselage:

Velocity Vector just below the Fuselage:

Pressure contour at XY plane:

Velocity contour at XY plane:

Pressure contour at YZ plane:

Velocity contour at YZ plane:

Pressure contour at Fuselage: