Getting the full benefits of CFD in conceptual design

Mason, William H.; Knill, Duane L.; Giunta, Anthony A.; Grossman, Bernard; Watson, Layne T.; Haftka, Raphael T.

doi:10.2514/6.1998-2513

Cited by 28 publications

(11 citation statements)

References 22 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Traditionally, wind-tunnel measurements are used to fill look-up tables of aerodynamic forces and moments related to the flight state. Windtunnel models only become available late in the design cycle and most data at the conceptual design stage relies on handbook methods or linear fluid mechanics assumptions [20,25,29]. These methods provide low cost reliable data only for conventional aircraft in aerodynamically benign regions of the flight envelope.…”

Section: Introductionmentioning

confidence: 99%

Automated CFD Analysis for the Investigation of Flight Handling Qualities

Ghoreyshi

Badcock

Ronch

et al. 2011

Math. Model. Nat. Phenom.

View full text Add to dashboard Cite

Abstract. Physics based simulation is widely seen as a way of increasing the information about aircraft designs earlier in their definition, thus helping with the avoidance of unanticipated problems as the design is refined. This paper reports on an effort to assess the automated use of computational fluid dynamics level aerodynamics for the development of tables for flight dynamics analysis at the conceptual stage. These tables are then used to calculate handling qualities measures. The methodological questions addressed are a)geometry and mesh treatment for automated analysis from a high level conceptual aircraft description and b) sampling and data fusion to allow the timely calculation of large data tables. The test case used to illustrate the approaches is based on a refined design passenger jet wind tunnel model. This model is reduced to a conceptual description, and the ability of this geometry to allow calculations relevant to the final design to be drawn is then examined. Data tables are then generated and handling qualities calculated.

show abstract

Section: Introductionmentioning

confidence: 99%

Automated CFD Analysis for the Investigation of Flight Handling Qualities

Ghoreyshi

Badcock

Ronch

et al. 2011

Math. Model. Nat. Phenom.

View full text Add to dashboard Cite

show abstract

“…Mason et al (1998) present a review of work on the conceptual design of a high speed civil transport (HSCT) aircraft, in which DoE, variable complexity analysis using the 'reasonable design space' approach (Balabanov et al 1999), and polynomial response surface modelling are used to incorporate high-fidelity analysis into conceptual design. Knill et al (1999) make use of the same HSCT problem to investigate using a low-fidelity model to decrease the number of terms used to build a polynomial RSM and so reduce the number of high-fidelity simulations required.…”

Section: Introductionmentioning

confidence: 99%

Optimization using surrogate models and partially converged computational fluid dynamics simulations

2006

View full text Add to dashboard Cite

Efficient methods for global aerodynamic optimization using computational fluid dynamics simulations should aim to reduce both the time taken to evaluate design concepts and the number of evaluations needed for optimization. This paper investigates methods for improving such efficiency through the use of partially converged computational fluid dynamics results. These allow surrogate models to be built in a fraction of the time required for models based on converged results. The proposed optimization methodologies increase the speed of convergence to a global optimum while the computer resources expended in areas of poor designs are reduced. A strategy which combines a global approximation built using partially converged simulations with expected improvement updates of converged simulations is shown to outperform a traditional surrogate-based optimization.

show abstract

“…To obtain optimal geometry for the UAV with respect to wing and tail design variables simultaneously, the optimiser had to find compromise solutions that included both wing surface area and tail volume [15,54]. Wing sizing is related to tail sizing, which has as its primary function the simultaneously countering of the moments that will be produced by the wing, and also satisfying stability requirements.…”

Section: Visualisation Of Results Using Parallel Coordinatesmentioning

confidence: 99%

“…The flow solver used here is the AVL. Due to the fluid nature of the initial design process, it is not recommended to use high fidelity analysis design tools, such as Computational Fluid Dynamics (CFD), at this stage as they can be unnecessarily costly [4,54]. What is required is a tool that strikes a balance between sufficient accuracy and computational cost [55][56][57][58].…”

Section: Particles Selection Schema On I-mopso Interfacementioning

confidence: 99%

The Interactive Design Approach for Aerodynamic Shape Design Optimisation of the Aegis UAV

2019

View full text Add to dashboard Cite

In this work, an interactive optimisation framework—a combination of a low fidelity flow solver, Athena Vortex Lattice (AVL), and an interactive Multi-Objective Particle Swarm Optimisation (MOPSO)—is proposed for aerodynamic shape design optimisation of any aerial vehicle platform. This paper demonstrates the benefits of interactive optimisation—reduction of computational time with high optimality levels. Progress towards the most preferred solutions is made by having the Decision Maker (DM) periodically provide preference information once the MOPSO iterations are underway. By involving the DM within the optimisation process, the search is directed to the region of interest, which accelerates the process. The flexibility and efficiency of undertaking optimisation interactively have been demonstrated by comparing the interactive results with the non-interactive results of an optimum design case obtained using Multi-Objective Tabu Search (MOTS) for the Aegis UAV. The obtained results show the superiority of using an interactive approach for the aerodynamic shape design, compared to posteriori approaches. By carrying out the optimisation using interactive MOPSO it was shown to be possible to obtain similar results to non-interactive MOTS with only half the evaluations. Moreover, much of the usual complexity of post-data-analysis with posteriori approaches is avoided, since the DM is involved in the search process.

show abstract

Getting the full benefits of CFD in conceptual design

Cited by 28 publications

References 22 publications

Automated CFD Analysis for the Investigation of Flight Handling Qualities

Automated CFD Analysis for the Investigation of Flight Handling Qualities

Optimization using surrogate models and partially converged computational fluid dynamics simulations

The Interactive Design Approach for Aerodynamic Shape Design Optimisation of the Aegis UAV

Contact Info

Product

Resources

About