'Aircraft_Landing_Gear' simulation project by Ali_Arafat


#1

I created a new simulation project called 'Aircraft_Landing_Gear':

This project simulates instantaneous air flow around an Aircraft Landing Gear.


More of my public projects can be found here.


#2

 

Description


 

 
As almost any pilot would declare, without a doubt, taking off is easy but landing is when their skills are actually tested. Coinciding the flight trajectory with the landing path and decelerating steadily require much flair and experience. More importantly, there is a great potential for damage to an aircraft due to a hard landing, or an improper landing technique.This may lead to a high stress (due to the air or land impact) on the tyres as well as the shock strut, causing them to wear out sooner or even fracture.
 
Computational Fluid Dynamics (CFD) may be used a tool to simulate and study the behavior of the aircraft landing gear in reaction to the stresses as an effect of the airflow against the motion of the airplane. The results of this study help us to compare different designs as well as various materials to be used for the multiple components that go into the simple looking but complicated structure.
 

Project Goals


 
This project proposes to conduct a CFD simulation of the airflow around the landing gear of an aircraft to achieve the resultant velocities and pressure acting (and hence, stress induced) on itself while in operation.

This configuration is simulated via the Large Eddy Simulation (LES) method.
 

Geometry


 
The geometry is a simplified version of the front landing gear configuration of a standard commercial aircraft.
 
image
 

Meshes


 
The domain is meshed using the Snappy-Hex-Mesh on the SimScale platform. The resulting mesh consists of approximately 1.8 million nodes and is shown in the figure below.
 


 

Simulations


 
Post the meshing process the simulation is set up using the Smagorinski model for the sub-grid-scales. The free stream flow velocity (Air) is set to be 35 m/s at standard conditions. A ramping of the velocity boundary condition was applied to gradually increase the velocity from a low value to free-stream value for faster convergence.
 

Results and Conclusions


 
The simulation analyzes the instantaneous velocity profiles and the wake vortices. The flow field is sufficiently developed for post processing of the results. The presented results (processed on ParaView) give an insight into the flow field in the wake regions.
 
Shown below are contours of velocity at sections in the stream-wise and span-wise directions along with the stream-lines and Iso-surfaces.
 
At Mid plane:


 
Sections in Z-direction:

 
Velocity Streamlines:

 
Iso-Contours: