Aerodynamic simulation of Bayraktar Akinci aircraft (UCAV) using Fluent

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In this project, Bayraktar Akinci aircraft (UCAV) is simulated using Fluent. Purchasing this product lets you access CAD and mesh files and simulated files. With the purchase of this product, a training video will be sent to you about the Fluent simulation steps and a full explanation of the options.

$25.00

Description

In this project, Bayraktar Akinci aircraft (UCAV) is simulated using Fluent. The Bayraktar Akinci is an uncrewed combat aerial vehicle (UCAV) produced by the Turkish defense company Baykar. It is the latest addition to Baykar’s Bayraktar drone family, following the highly successful Bayraktar TB2. The Akinci is a heavy-class drone with a maximum takeoff weight of 5,500 kilograms and a wingspan of 20 meters. It is powered by two turboprop engines and has an endurance of up to 24 hours. The drone has a maximum altitude of 40,000 feet and can carry up to 1,350 kilograms of weapons.

One of the unique features of the Akinci is its flexibility. It can be configured for various missions, ranging from surveillance and reconnaissance to ground attack and even air-to-air combat. The drone has multiple sensors and weapons, including synthetic aperture radar, electro-optical/infrared sensors, laser-guided missiles, and air-to-air missiles. The Akinci has already undergone successful flight tests, with the first flight in December 2019. It is expected to enter service with the Turkish Armed Forces shortly and has already generated interest from potential export customers. Overall, the Bayraktar Akinci is a highly capable UCAV that significantly boosts air power for any nation that operates it.

Method:

This simulation has been performed in 3D, and its geometry has been created using Space Claim software. Ansys Meshing software has carried out the meshing of this geometry, and the number of elements used for this project is 194080.

This simulation has been performed under a steady state, and the solution method used to solve the equations is the coupled method.

The inlet boundary conditions are of the velocity inlet type, with a magnitude of 100 meters per second. For the outlet boundary, it is of the pressure outlet type with a gauge pressure of zero pascals.

Result:

After the simulation, we can observe velocity and pressure contours and calculate aerodynamic coefficients such as lift and drag.

 Convergence plot:

residual

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