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Optimum aerodynamic design using the NavierStokes equations
 Theoretical and Computational Fluid Dynamics
, 1998
"... The ultimate success of an aircraft design depends on the resolution of complex multidisciplinary tradeo s between factors such as aerodynamic eciency, structural weight, stability and control, and ..."
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Cited by 107 (45 self)
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The ultimate success of an aircraft design depends on the resolution of complex multidisciplinary tradeo s between factors such as aerodynamic eciency, structural weight, stability and control, and
Aerodynamic Design Optimisation for Complex Geometries Using Unstructured Grids
, 1997
"... this paper are from the last 5 years, and it can be expected that there will be signi cant new developments in the next 5 years ..."
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Cited by 2 (1 self)
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this paper are from the last 5 years, and it can be expected that there will be signi cant new developments in the next 5 years
Automatic Differentiation and Sensitivity Analysis Methods for Computational Fluid Dynamics
 QUB SCHOOL OF AERONAUTICAL ENGINEERING
, 2003
"... ..."
Aerospace Design: A Complex Task
, 1997
"... Introduction 1.1 Design The objective of engineering analysis, the mathematical and computational modelling of an engineering product, is not to determine the behaviour of a single product; if this were the case it would be simpler and cheaper to take the first manufactured product and test it ext ..."
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Introduction 1.1 Design The objective of engineering analysis, the mathematical and computational modelling of an engineering product, is not to determine the behaviour of a single product; if this were the case it would be simpler and cheaper to take the first manufactured product and test it extensively. The real objective of engineering analysis is to predict the behaviour of a product, and then use that information to design a better product. Often a whole sequence of improved designs is created, with very few being actually manufactured and tested experimentally. Given that experimental testing is often very timeconsuming and expensive, the extensive use of computational engineering analysis can greatly reduce the time and cost of the design process. Although design is the ultimate objective of engineering analysis, most academic research in the past 20 years has been directed towards the simpler task of modelling the behaviour of specific aspects of the engineering system. Th
AIAA20025435 IMPLICIT AND EXPLICIT SENSITIVITIES FOR OPTIMIZATION OF COOLED TURBINE BLADES
"... The partial derivatives of field variables (temperatures, temperature gradients, thermal conductivity, heat sources. etc.) and boundary values (heat fluxes, heat transfer coefficients, heat radiation, etc.) with respect to the perturbations of the boundary conditions and geometry are very useful whe ..."
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The partial derivatives of field variables (temperatures, temperature gradients, thermal conductivity, heat sources. etc.) and boundary values (heat fluxes, heat transfer coefficients, heat radiation, etc.) with respect to the perturbations of the boundary conditions and geometry are very useful when performing a parametric study of a particular design. These partial derivatives are called design sensitivity coefficients. The implementation of gradientbased algorithms for inverse thermal shape design and numerical optimization require these partial derivatives as part of their operation. But the computer generation of these sensitivity coefficients can use up a great deal of computer resources and processing time. In order to make computerautomated optimization practicable in the design environment of the highly competitive turbomachinery industry, any reduction in resources, time and manpower should be attempted. Implicit differentiation of the aerodynamic, structural and thermal simulation codes can provide a significant reduction in the computerprocessing time, resulting in faster turnaround times by the optimization team. It makes the use of optimization in the standard design practices of the company not only viable, but also it can reduce the design cycle time, achieve an optimal design, and make the company more competitive. Copyright @2002 by Thomas J. Martin. Published by the
Theoretical and Computational Fluid Dynamics © SpringerVerlag 1998 Optimum Aerodynamic Design Using the Navier–Stokes Equations 1
, 1997
"... Abstract. This paper describes the formulation of optimization techniques based on control theory for aerodynamic shape design in viscous compressible flow, modeled by the Navier–Stokes equations. It extends previous work on optimization for inviscid flow. The theory is applied to a system defined b ..."
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Abstract. This paper describes the formulation of optimization techniques based on control theory for aerodynamic shape design in viscous compressible flow, modeled by the Navier–Stokes equations. It extends previous work on optimization for inviscid flow. The theory is applied to a system defined by the partial differential equations of the flow, with the boundary shape acting as the control. The Fréchet derivative of the cost function is determined via the solution of an adjoint partial differential equation, and the boundary shape is then modified in a direction of descent. This process is repeated until an optimum solution is approached. Each design cycle requires the numerical solution of both the flow and the adjoint equations, leading to a computational cost roughly equal to the cost of two flow solutions. The cost is kept low by using multigrid techniques, in conjunction with preconditioning to accelerate the convergence of the solutions. The power of the method is illustrated by designs of wings and wing–body combinations for long range transport aircraft. Satisfactory designs are usually obtained with 20–40 design cycles. 1.