Aerodynamic design optimization using sensitivity analysis and computational fluid dynamics

Baysal, Oktay; Eleshaky, Mohamed E.

doi:10.2514/6.1991-471

Cited by 46 publications

(22 citation statements)

References 2 publications

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“…5 A simpli ed scramjet-afterbody con guration has been optimized for axial thrust, using sensitivity analysis and analytical expressions for derivatives used in the optimization. 6 Optimization techniques based on control theory, which use adjoint equations for gradient calculation, are used for aerofoil and wing design. 7,8 We have developed a prototype software system that combines Navier -Stokes simulations and numerical optimization methods.…”

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confidence: 99%

Automated Design Optimization for the P2 and P8 Hypersonic Inlets

Shukla

Gelsey

Schwabacher

et al. 1997

Journal of Aircraft

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An automated design methodology incorporating industry-standard Navier -Stokes codes and a gradient-based optimizer has been developed. This system is used to redesign the well-known NASA P2 and P8 hypersonic inlets. First, the Navier -Stokes simulations of the original P 2 and P8 inlet designs are validated using numerical convergence studies and comparison with wind-tunnel experimental data for the original inlets published by NASA in the early 1970s. Second, the P 2 and P8 inlets are redesigned with the objective of canceling the cowl shock (and, in the case of the P8 inlet, the additional cowlgenerated compression) at the centerbody by appropriate contouring of the centerbody boundary. The original inlets were intended to achieve these same objectives, but detailed experimental measurements indicated that a substantial re ected shock system was present. The choice of the objective function, which is used to drive the optimization, has a signi cant impact on the nal design. Several different formulations for the objective function have been employed, and improvements of 60 -90% in the objective function have been achieved. This automated design system represents one of the rst successful combinations of numerical optimization methods with Reynolds-averaged Navier -Stokes uid dynamics simulation for high-speed inlets, and demonstrates a new area in which high-performance computing may have considerable impact on problems of military and industrial signi cance. Nomenclature

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confidence: 99%

Automated Design Optimization for the P2 and P8 Hypersonic Inlets

Shukla

Gelsey

Schwabacher

et al. 1997

Journal of Aircraft

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“…This line of research started in the 1970's with Pironneau's study of control theory applied to shape optimization [13,14], and was followed by Jameson's seminal work on aerodynamic design [15,16]. These methods have received significant research attention [17][18][19], and are the state of the art for high-fidelity aero-structural optimization [20,21]. Finally, there is recent interest in multi-fidelity methods [22], where inexpensive models could guide which high-fidelity analyses to conduct.…”

Section: Introductionmentioning

confidence: 99%

Geometric Programming for Aircraft Design Optimization

Hoburg

Abbeel

2014

AIAA Journal

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We propose formulating conceptual-stage aircraft design problems as geometric programs (GPs), which are a specific type of convex optimization problem. Recent advances in convex optimization offer significant advantages over the general nonlinear optimization methods typically used in aircraft design. Modern GP solvers are extremely fast, even on large problems, require no initial guesses or tuning of solver parameters, and guarantee globally optimal solutions. These benefits come at a price: all objective and constraint functions -the mathematical models that describe aircraft design relations -must be expressed within the restricted functional forms of GP. Perhaps surprisingly, this restricted set of functional forms appears again and again in prevailing physics-based models for aircraft systems. Moreover, we show that for various models that cannot be manipulated algebraically into the forms required by GP, we can often fit compact GP models which accurately approximate the original models. The speed and reliability of GP solution methods makes them a promising approach for conceptual-stage aircraft design problems.

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“…Multi-objective design optimization in aerodynamics and electro-magnetics was carried out by Mäkinen et al (1998). Various non-linear problems in general fluid flow had been optimized using gradient-based optimization tools by several investigators (Baysal and Eleshaky, 1992;Reuther et al, 1999aReuther et al, , 1999bBängtsson, Noreland and Berggren, 2003;Mohammadi, Molho and Santiago, 2003). The shape of cut-off in a multi-blade fan/scroll system was optimized by Han and Maeng (2003) using CFD.…”

Section: Introductionmentioning

confidence: 99%

Optimum Design of a Two Step Planar Diffuser: A Hybrid Approach

Ghosh

Pratihar

Maiti

et al. 2010

Engineering Applications of Computational Fluid Mechanics

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This study attempts to optimize a planar diffuser with two steps using a hybrid approach. It uses CFD softwares: Gambit for mesh generation, Fluent for carrying out hydrodynamic analysis, and employs a Genetic Algorithm (GA) for optimization. Here, the GA and CFD softwares combine each other seamlessly and exchange data among the commercial softwares (namely Gambit and Fluent) and optimization tool (that is, GA) in a fully automated manner without any human intervention. The hydrodynamic analysis is used to calculate pressure drop across the diffuser for a fully turbulent flow, while the GA determines its optimum design, which minimizes the same. The optimum dimensions of the diffuser wall have been determined for different values of Reynolds number and area ratios between the outlet and inlet of the diffuser. Finally, relationships of optimum geometrical dimensions with the Reynolds number and area ratio have been developed for the ready use of designers.

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Aerodynamic design optimization using sensitivity analysis and computational fluid dynamics

Cited by 46 publications

References 2 publications

Automated Design Optimization for the P2 and P8 Hypersonic Inlets

Automated Design Optimization for the P2 and P8 Hypersonic Inlets

Geometric Programming for Aircraft Design Optimization

Optimum Design of a Two Step Planar Diffuser: A Hybrid Approach

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