A machine learning enhanced discontinuous Galerkin method for simulating transonic airfoil flow-fields

TL;DR

This paper introduces a machine learning-enhanced discontinuous Galerkin method that rapidly and accurately simulates transonic airfoil flow-fields by combining data-driven models with traditional numerical techniques.

Contribution

It develops a novel hybrid approach integrating a lightweight data-driven model with DGM, improving simulation speed and accuracy for transonic flows across various conditions.

Findings

Accurately predicts flow-fields for Mach 0.7 to 0.95 and -5° to 5° angles of attack.

Significantly improves computational efficiency over standard DGM.

Maintains high accuracy in flow structure features like shock waves.

Abstract

Accurate and rapid prediction of flow-fields is crucial for aerodynamic design. This work proposes a discontinuous Galerkin method (DGM) whose performance enhances with increasing data, for rapid simulation of transonic flow around airfoils under various flow conditions. A lightweight and continuously updated data-driven model is built offline to predict the roughly correct flow-field, and the DGM is then utilized to refine the detailed flow structures and provide the corrected data. During the construction of the data-driven model, a zonal proper orthogonal decomposition (POD) method is designed to reduce the dimensionality of flow-field while preserving more near-wall flow features, and a weighted-distance radial basis function (RBF) is constructed to enhance the generalization capability of flow-field prediction. Numerical results demonstrate that the lightweight data-driven model can predict the flow-field around a wide range of airfoils at Mach numbers ranging from 0.7 to 0.95 and angles of attack from -5 to 5 degrees by learning from sparse data, and maintains high accuracy of the location and essential features of flow structures (such as shock waves). In addition, the machine learning (ML) enhanced DGM is able to significantly improve the computational efficiency and simulation robustness as compared to normal DGMs in simulating transonic inviscid/viscous airfoil flow-fields on arbitrary grids, and further enables rapid aerodynamic evaluation of numerous sample points during the surrogate-based aerodynamic optimization.