Bayraktar UAV Simple Aerodynamic Analysis: CFD Simulation by ANSYS Fluent
Price: $219
- The problem numerically simulates a Skywalker X8 UAV using ANSYS Fluent software.
- We design the 3-D model with the Design Modeler software.
- We mesh the model with Fluent Meshing software. The element number equals 1,199,753 and their type is polyhedra.
- Multiple Reference Frames (Frame Motion) are used to model the rotational motion of the propeller.
Bayraktar UAV Simple Aerodynamic Analysis: CFD Simulation by ANSYS Fluent
Price: $219
- The problem numerically simulates a Skywalker X8 UAV using ANSYS Fluent software.
- We design the 3-D model with the Design Modeler software.
- We mesh the model with Fluent Meshing software. The element number equals 1,199,753 and their type is polyhedra.
- Multiple Reference Frames (Frame Motion) are used to model the rotational motion of the propeller.
Simple Aerodynamic Analysis: Bayraktar UAV CFD Simulation Training
Introduction
An unmanned aerial vehicle from Turkey is called the Bayraktar. It is a long-lasting, medium-altitude drone. It can be used for surveillance and reconnaissance.
It has a top speed of more than 220 kilometers per hour. The drone has a fuel capacity of 300 liters. The range can go up to 300 km. 5.48 kilometers is the operational altitude. The greatest height is 7.62 kilometers Maximum loitering time for this drone is 27 hours.
In this simulation, a Bayraktar UAV with one propeller rotating around the horizontal axis is modeled using ANSYS Fluent software. The device is moving at a speed of 140 km/h.
The geometry of the present model is three-dimensional and has been designed using Design Modeler software. We do the meshing of the present model with Fluent Meshing software. The mesh type is Polyhedra, and the element number is 1,199,753.
Methodology: Bayraktar UAV CFD Simulation
The Multiple Reference Frames (MRF) method is used to model the rotational motion of the propeller.
Conclusion
Following the completion of the simulation process, vectors and contours for variables like pressure, velocity and turbulent intensity were acquired. The vortexes behind the propeller are visible, as evidenced by the velocity contours. Good dynamic stability is obtained as a result of the Reverse V- tale opposition to the vortexes.
In the static pressure parameter case, as it was predictable, the UAV's front surfaces endure the highest pressure. The maximum static pressure is applied to the propellers' edges, which tells us about the necessity of the manufacturing focus on this component.