We present simultaneous pseudo-timestepping as an efficient method for aerodynamic shape optimization. In this method, instead of solving the necessary optimality conditions by iterative techniques, pseudo-time embedded nonstationary system is integrated in time until a steady state is reached. The main advantages of this method are that it requires no additional globalization techniques and th...

Two unstructured-grid Euler-based CFD codes, AIRPLANE and FLOWCART were coupled to a gradientbased quasi-Newton finite-difference optimization algorithm. These two optimization techniques were developed to provide detailed aerodynamic shape optimization methods for complete configurations with efficient grid generation methods. AIRPLANE utilizes a tetrahedral mesh whereas FLOWCART uses a hexahe...

An objective of the High Performance Computing and Communication Program at the NASA Langley Research Center is to demonstrate multidisciplinary shape and sizing optimization of a complete aerospace vehicle configuration by using high-fidelity finiteelement structural analysis and computational fluid dynamics aerodynamic analysis in a distributed, heterogeneous computing environment that includ...

The symbol of the Hessian for a static aeroelastic optimization model problem is analyzed for the optimization of a plate's shape and rigidity distribution with respect to a given cost function. The ow is modeled by the small-disturbance full-potential equation and the structure is modeled by an isotropic (von K arm an) plate equation. The cost function consists of both aerodynamic and structur...

This study deals with the use of optimization algorithms to determine efficient parameters of flow control devices. To improve the performance of systems characterized by detached flows and vortex shedding, the use of flow control devices such as oscillatory jets, are intensively studied, using numerical as well as experimental methods. However, the determination of efficient control parameters...

We present an optimization algorithm for the study of induced drag minimization, with applications to unconventional aircraft design. The algorithm is based on a discrete-adjoint formulation and uses an efficient parallel-Newton-Krylov solution strategy. We validate the optimizer by recovering an elliptical lift distribution using twist optimization; we believe this an important, and under-appr...

Adaptive mesh refinement is one of the most important tools in Computational Fluid Dynamics (CFD) for solving complex engineering design problems. The paper investigates two practical transonic aerofoil design optimization problems using a genetic algorithm coupled with an Euler aerodynamic analysis tool. The first problem consists in the minimization of transonic drag whereas the second is a r...

This paper focuses on the demonstration of an integrated aero-structural method for the design of aerospace vehicles. Both aerodynamics and structures are represented using high-fidelity models such as the Euler equations for the aerodynamics and a detailed finite element model for the primary structure. The aerodynamic outer mold line (OML) and a structure of fixed topology are parameterized u...

in this paper, an optimization method for both weight and displacement of composite blades is presented. in   order to hold issues such as aerodynamics and acoustic unchanged, airfoil shape during optimization process remained constant. to achieve the ultimate goal, only blade lamination was changed. in order to achieve minimum weight for each part of the structure, the lowest layers are foreca...