Constrained multipoint aerodynamic shape optimization using an adjoint formulation and parallel computers

Reuther, James; Jameson, Antony; Alonso, Juan J.; Rimlinger, Mark J.; Sauders, D.

doi:10.2514/6.1997-103

Cited by 103 publications

(106 citation statements)

References 18 publications

Supporting

Mentioning

106

Contrasting

Order By: Relevance

“…This tool couples the multiblock Euler and Navier Stokes flow solver FLO107-MB 16 to an H-mesh generator adapted from the HFLO4 code of Jameson and Baker, 17 and to the PC Boom software for far field propagation developed by Wyle Associates. The H-type mesh, which is generated automatically from the geometric definition, can handle arbitrary wing-fuselage-canard configurations.…”

Section: Nonlinear Integrated Boom Analysis Environmentmentioning

confidence: 99%

“…Vehicle shape modification that leads to reduced boom overpressures for a specific design often results in degraded aerodynamic performance 4 and so boom reduction must be considered as one aspect of a multidisciplinary design problem. Our group has had considerable experience in aerodynamic shape optimization and multidisciplinary aircraft design, [5][6][7][8][9][10][11][12][13][14][15] and the combination of these two research areas represents an opportunity for further advances.…”

mentioning

confidence: 99%

See 1 more Smart Citation

Advanced algorithms for design and optimization of Quiet Supersonic Platforms

Alonso

Jameson²,

Kroo³

2002

40th AIAA Aerospace Sciences Meeting &Amp; Exhibit

Self Cite

View full text Add to dashboard Cite

This paper describes the work carried out within the Stanford University group as part of the DARPA-funded Quiet Supersonic Platform (QSP) project. The objective of our work was to develop advanced numerical methods to facilitate the analysis and design of low sonic boom aircraft. The focus of the boom reduction activities was placed on two main ideas: the shaping of the configuration and a multidisciplinary design approach to minimize its total empty weight. Accurate and efficient tools are needed to achieve these tasks. Our approach was meant to enhance the existing state-of-the-art which was developed in the 1970s and during the early stages of the High Speed Research (HSR) program. For that purpose, we designed tools that would ultimately become fully nonlinear (in contrast with current design efforts based on linear theories of the 1970s). These tools are also able to account for important tradeoffs between boom reduction and aerodynamic perormance, as well as other disciplines. Because of the difficulty of the problem, the tools were designed to support a combination of gradient and non-gradient automatic optimization techniques. As a result of our efforts, rapid turnaround boom analysis and design methods were developed. These methods permit the investigation of radical configuration changes and their effect on the ground boom signature and the L/D ratio of the aircraft. We have also created an environment for the automatic nonlinear analysis of QSP configurations based on the multiblock flow solver FLO107-MB. In addition, we have extended the adjoint-based design method to treat remote sensitivities to near-field pressure signatures, allowing for a very large number of parameters to be used in modifications of the aircraft geometry. All tools were carefully validated against existing experimental data, other boom prediction programs, and with systematic mesh refinement studies.

show abstract

Section: Nonlinear Integrated Boom Analysis Environmentmentioning

confidence: 99%

mentioning

confidence: 99%

Advanced algorithms for design and optimization of Quiet Supersonic Platforms

Alonso

Jameson²,

Kroo³

2002

40th AIAA Aerospace Sciences Meeting &Amp; Exhibit

Self Cite

View full text Add to dashboard Cite

show abstract

“…Jameson et al 8 first applied this method to transonic flow. In the last seven years, automatic aerodynamic design of complete aircraft configurations has yielded optimized solutions of wing and wing-body configu-rations by Reuther et al 13,14 and Burgreen et al…”

Section: Introductionmentioning

confidence: 99%

Studies of the continuous and discrete adjoint approaches to viscous automatic aerodynamic shape optimization

Nadarajah

Jameson

2001

15th AIAA Computational Fluid Dynamics Conference

View full text Add to dashboard Cite

This paper compares the continuous and discrete viscous adjoint-based automatic aerodynamic optimization. The objective is to study the complexity of the discretization of the adjoint equation for both the continuous and discrete approach, the accuracy of the resulting estimate of the gradient, and its impact on the computational cost to approach an optimum solution. First, this paper presents complete formulations and discretizations of the NavierStokes equations, the continuous viscous adjoint equation and its counterpart the discrete viscous adjoint equation. The differences between the continuous and discrete boundary conditions are also explored. Second, the accuracy of the sensitivity derivatives obtained from continuous and discrete adjoint-based equations are compared to complexstep gradients. Third, the adjoint equations and its corresponding boundary conditions are formulated to quantify the influence of geometry modifications on the pressure distribution at an arbitrary remote location within the domain of interest. Finally, applications are presented for inverse, pressure and skin friction drag minimization, and sonic boom minimization problems.

show abstract

“…This method was first applied to transonic flow by Jameson et al [6]. In the last six years automatic aerodynamic design of complete aircraft configurations has yielded optimized solutions of wing and wing-body configurations by Reuther et al [11,12] and Burgreen et al [13].…”

Section: Introductionmentioning

confidence: 99%

An adjoint method for the calculation of non-collocated sensitivities in supersonic flow

Nadarajah¹,

Jameson²,

Alonso³

2001

Computational Fluid and Solid Mechanics

View full text Add to dashboard Cite

This paper presents an adjoint method for the calculation of non-collocated sensitivities in supersonic flow. The goal is to develop a set of discrete adjoint equations and their corresponding boundary conditions in order to quantify the influence of geometry modifications on the pressure distribution at an arbitrary location within the domain of interest. First, this paper presents the complete formulation and discretization of the discrete adjoint equations.The special treatment of the adjoint boundary condition to obtain non-collocated sensitivities is also discussed. Second, we present results that demonstrate the application of the theory to a two-dimensional inverse design problem using the traditional Ni-bump geometry.

show abstract

Constrained multipoint aerodynamic shape optimization using an adjoint formulation and parallel computers

Cited by 103 publications

References 18 publications

Advanced algorithms for design and optimization of Quiet Supersonic Platforms

Advanced algorithms for design and optimization of Quiet Supersonic Platforms

Studies of the continuous and discrete adjoint approaches to viscous automatic aerodynamic shape optimization

An adjoint method for the calculation of non-collocated sensitivities in supersonic flow

Contact Info

Product

Resources

About