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Helicopter CFD Simulation by Transient Solver, ANSYS Fluent Training

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In this project, rotation of helicopter wings are simulated in transient time formulation and the results including net upward force, wing tip speed and Tip Speed Ratio (TSR) are investigated applying Mesh Motion (Moving Mesh) method.

This product includes a Mesh file and a comprehensive Training Movie.

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Description

Problem description

In this project, rotation of helicopter wings are simulated in transient time formulation and the results including net upward force, wing tip speed and Tip Speed Ratio (TSR) are investigated. In order to generate upward movement in aerodynamic applications, movement of certain amount of air in downward direction is needed, which in return generates upward motion. For helicopters, this movement of air is done using a propeller which consists of 2 or more wing shaped geometries, rotating around a center. Propeller is aerodynamically designed in a way that forces air to flow over it and increases the air pressure under the wing. In this simulation, propeller is rotating with angular velocity equal to 1250 rpm in –Y direction.

Helicopter Geometry and mesh

Geometry of fluid domain is designed in Design Modeler and computational grid is generated using ANSYS Meshing. Mesh type is unstructured and element number is 937677.

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Solver configuration for Helicopter CFD Simulation

Critical assumptions:

  • Solver type is pressure-Base.
  • Time formulation is assumed transient.
  • Gravity effects are neglected.

The following table a summary of the defining steps of the problem and its solution.

Models
Viscous K-epsilon model RNG
Near wall treatment standard wall treatment
Materials
Fluid Definition method Fluent Database
Material name Air
Cell zone conditions
Torot Mesh motion 1250 rpm
Axis -Y direction
Center of rotation (-0.003,0,0.0002)
Boundary conditions
Walls symmetry
Solver configurations
Formulation Implicit SIMPLE
Spatial discretization Gradient Least square cell-based
Pressure Second order
Momentum Second order Upwind
K First order Upwind
Epsilon First order Upwind

Results and discussion

Pressure difference between under and over the helicopter geometry is equal to 5 Pa. Maximum air velocity in domain is equal to 2 m/s. Air velocity at wing tip, which has the maximum velocity magnitude on the wing length, is equal to 1.96 m/s.

There are a Mesh file and a comprehensive Training Movie that presents how to solve the problem and extract all desired results.

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