We present a parallel adjoint framework for aerodynamic shape optimization problems using an embedded-boundary Cartesian mesh method. The design goals for the framework focus on an efficient and systematic integration of the underlying software modules. By linearizing the geometric constructors used in intersecting triangulated components, we develop a robust approach for computing surface shap...

Computational fluid dynamic (CFD) models are ubiquitous in aerodynamic design. Variable-fidelity optimization algorithms have proven to be computationally efficient and therefore suitable to reduce high CPU-cost related to the design process solely based on accurate CFD models. A convenient way of constructing the variable-fidelity models is by using the high-fidelity solver, but with a varying...

Improving the efficiency of compressors has been one of the most important goals of researchers over the years. In this paper, three different methods are presented for parameterization and blade optimization of axial flow compressor. All methods consist of flow analysis tool, optimization algorithms, and parametric geometry generation tool, that are different in each approach. Objective functi...

Differential Evolution (DE) is a simple and robust evolutionary strategy that has been proven effective in determining the global optimum for several difficult optimization problems. Although DE offers several advantages over traditional optimization approaches, its use in applications such as aerodynamic shape optimization where the objective function evaluations are computationally expensive ...

For complicated aerodynamic design problems, the efficient global optimization method suffered from defect of incorrect portrayal space, resulting in bad convergence and efficiency performance. To this end, a Kriging-based method, named space exploration (KSE), was proposed paper. It selected multiple promising local minima classified them into partially fully explored terms fitting quality sur...

A two-dimensional Newton–Krylov aerodynamic shape optimization algorithm is applied to several optimization problems in which the location of laminar-turbulent transition is free. The coupled Euler and boundary-layer solver MSES is used to obtain transition locations through the e method, which are then used in Optima2D, a Newton–Krylov discrete-adjoint optimization algorithm based on the compr...

Reducing fuel consumption and improving the economy by effectively reducing cruising drag is main objective of aerodynamic design supersonic civil aircraft. In this paper, optimization system based on Reynolds-Averaged Navier–Stokes (RANS) equation discrete adjoint theory applied to wing design. Based system, a single-point study reduction in cruise conditions was carried out for two typical la...