Aerodynamic Optimization of Airfoil Shape for Subsonic, Transonic, Supersonic and Hypersonic Speeds

Bernardo Cardoso Leite

Key information

Authors:

Bernardo Cardoso Leite (Bernardo Cardoso Leite)

Supervisors:

Frederico José Prata Rente Reis Afonso (Frederico Afonso); Afzal Suleman (Afzal Suleman)

Published in

July 15, 2022

Abstract

Hypersonic flight has been the subject of numerous research programs throughout the last eight decades. This work aims to study and optimize the aerodynamic performance of a two-dimensional baseline airfoil (NACA0012) at distinct speeds within the framework of a hypersonic transport aircraft. Hence, a mission profile has been defined, from which four points representing the subsonic (Mach=0.5), transonic (Mach=1.0), supersonic (Mach=2.0), and hypersonic (Mach=6.0) flow conditions have been selected. To carry out the flow study and optimization procedures, a methodology has been implemented based on CFD simulations performed on the high-fidelity solver SU2, where RANS equations have been chosen as governing equations together with SA as turbulence model. The computational mesh has been generated via GMSH, followed by a Grid Convergence Study, which has ensured spatial convergence and grid-independent numerical results for each of the speed regimes. Gradient-based optimizations have been conducted using drag as the objective function to be minimized, as well as the Free-Form Deformation technique as the parameterization method. Moreover, an additional optimization for the hypersonic case has been carried out using a Genetic Algorithm approach and Local Piston Theory. The optimization results show an overall improvement in aerodynamic performance, including decreases in the drag coefficient up to 79.2%. In the end, a morphing strategy has been laid out based on the optimal shapes produced by optimizations.