Eventos Anais de eventos
COBEM 2021
26th International Congress of Mechanical Engineering
THERMAL NUMERICAL ANALYSIS OF AN AIRCRAFT WING USING AN UNSTRUCTURED MESH IN CUDA-C
Submission Author:
Durval Marques de Queiroz Neto , SP
Co-Authors:
Durval Marques de Queiroz Neto, Elisan dos Santos Magalhães
Presenter: Durval Marques de Queiroz Neto
doi://10.26678/ABCM.COBEM2021.COB2021-0092
Abstract
The ice formation problem on aircraft wings is a primary safety concern for manufacturers. Thus, it is crucial to know the temperature profile in the wing section. This work presents a thermal numerical analysis performed on an aircraft wing using parallel programming on a GPU (Graphics Processing Unit). The model evaluates the heat exchange with the environment and the temperature profile within the wing by solving the heat diffusion equation. The mode considered the following boundary conditions: the prescribed temperature at the external surface and an imposed heat flux at the internal surface. The prescribed heat input condition simulates an ice protecting system commonly found in aircraft. An in-house CUDA-C code was developed to solve the two-dimensional heat transfer problem using a finite volume approach for the aircraft wing. In order to account for the wing profile, the model applied unstructured mesh. An independence mesh test was conducted to verify the solution. The results have shown the temperature profile for the wing tank. The results have shown that the GPU effectively performs the solution in almost real-time for a refined mesh. The main advantage of running the model in parallel within the GPU is the higher number of cores processing the problem, reducing the computational time associated cost needed to solve the problem and allowing more complex problems to be solved in commercial computers instead of clusters.
Keywords
CUDA, Heat flux, aircraft wing, parallel processing, heat conduction
