Low-Boom Design Optimization for SST Canard-Wing-Fuselage Configuration

Sasaki, Daisuke; Obayashi, Shigeru

doi:10.2514/6.2003-3432

Cited by 12 publications

(9 citation statements)

References 15 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Two test cases were considered, each one having different upper/lower limits for the section nearby the wing-body intersection. 2) Sasaki and Obayashi [147] solved a problem similar to the previous one [146] and obtained analogous results, but in this case, the ARMOGA algorithm was used. Also, and in order to incorporate constraints, an extended Pareto ranking method based on constraint-dominance was used [47].…”

Section: -D Complex Physics/shape Optimizationmentioning

confidence: 90%

“…The lack of modern diversity maintenance approaches such as archiving techniques [60], [94], [151] is also evident within the applications of this section, although there are some interesting exceptions. For example, Sasaki and Obayashi [147] adopted two external archives for their MOEA. Also interesting is the proposal of Holst [61] of using "bins" (this approach is similar in its operation to the adaptive grid adopted in PAES [83]).…”

Section: -D Complex Physics/shape Optimizationmentioning

confidence: 99%

See 1 more Smart Citation

Multiobjective Evolutionary Algorithms in Aeronautical and Aerospace Engineering

Arias-Montaño

Coello

Mezura-Montes

2012

IEEE Trans. Evol. Computat.

130

View full text Add to dashboard Cite

Nowadays, the solution of multiobjective optimization problems in aeronautical and aerospace engineering has become a standard practice. These two fields offer highly complex search spaces with different sources of difficulty, which are amenable to the use of alternative search techniques such as metaheuristics, since they require little domain information to operate. From the several metaheuristics available, multiobjective evolutionary algorithms (MOEAs) have become particularly popular, mainly because of their availability, ease of use, and flexibility. This paper presents a taxonomy and a comprehensive review of applications of MOEAs in aeronautical and aerospace design problems. The review includes both the characteristics of the specific MOEA adopted in each case, as well as the features of the problems being solved with them. The advantages and disadvantages of each type of approach are also briefly addressed. We also provide a set of general guidelines for using and designing MOEAs for aeronautical and aerospace engineering problems. In the final part of the paper, we provide some potential paths for future research, which we consider promising within this area.

show abstract

Section: -D Complex Physics/shape Optimizationmentioning

confidence: 90%

Section: -D Complex Physics/shape Optimizationmentioning

confidence: 99%

Multiobjective Evolutionary Algorithms in Aeronautical and Aerospace Engineering

Arias-Montaño

Coello

Mezura-Montes

2012

IEEE Trans. Evol. Computat.

130

View full text Add to dashboard Cite

show abstract

“…First, a response surface model was generated based on an initial database. A genetic optimization algorithm Contouring on a shrouded compressor stator 91 (Adaptive Range Multi-Objective Algorithm, ARMOGA [27]) was then applied to this response surface, the resulting parameter set was run in CFD and the response surface was updated with the result. The entire process was controlled by the optimization platform SOFT, another in-house tool.…”

Section: Endwall Contour Designmentioning

confidence: 99%

Numerical investigation of the influence of non-axisymmetric hub contouring on the performance of a shrouded axial compressor stator

et al. 2011

View full text Add to dashboard Cite

This numerical study uses a two-stage low speed research compressor with a shrouded stator row to investigate the interaction of non-axisymmetric endwall contouring at the stator hub with the leakage flow emanating from the shroud cavity. It can be shown that the contour is effective in reducing the hub corner stall caused by the separating endwall boundary layer. The leakage flow itself is not reduced. Subsequently, the height of the shroud seal fins is varied. A comparison of the results with and without non-axisymmetric endwalls shows that the effectiveness of the endwall contour in improving stator performance increases with the amount of leakage flow. Consequently, the sensitivity towards shroud leakage is decreased with contoured endwall. This leads to the conclusion that this design feature does not only serve to improve the flow quality in a given case, but also provides a means to the aerodynamic designer to introduce more robustness into the compressor.

show abstract

“…The real-coded ARGA has been successfully applied to airfoil design optimization, 24 wing design optimization, 25 and multiobjective supersonic transport design optimizations. 26 In the following paragraphs, we describe the steps used in this EA. Figure 6 shows a flowchart of the present real-coded ARGA.…”

Section: Easmentioning

confidence: 99%

Transonic Axial-Flow Blade Optimization: Evolutionary Algorithms/Three-Dimensional Navier-Stokes Solver

Oyama

Liou

Obayashi

2004

Journal of Propulsion and Power

Self Cite

107

View full text Add to dashboard Cite

Low-Boom Design Optimization for SST Canard-Wing-Fuselage Configuration

Cited by 12 publications

References 15 publications

Multiobjective Evolutionary Algorithms in Aeronautical and Aerospace Engineering

Multiobjective Evolutionary Algorithms in Aeronautical and Aerospace Engineering

Numerical investigation of the influence of non-axisymmetric hub contouring on the performance of a shrouded axial compressor stator

Transonic Axial-Flow Blade Optimization: Evolutionary Algorithms/Three-Dimensional Navier-Stokes Solver

Contact Info

Product

Resources

About