Common computational model for coupling panel method with finite element method

Abstract

Purpose Conceptual and preliminary aircraft concepts are getting mature earlier in the design process, than ever before. To achieve that advanced level of maturity, multiple multidisciplinary analyses have to be done, often with usage of numerical optimization algorithms. This calls for right tools that can handle such a demanding task. Often the toughest part of a modern design is handling an aircraft’s computational models used for different analysis. Transferring geometry and loads from one program to another, or modifying internal structure, takes time and is not productive. Authors defined the concept of a common computational model (CCM), which couples programs from different aerospace scientific disciplines. Data exchange between the software components is compatible, and multidisciplinary analysis can be automated to high degree, including numerical optimization. Design/methodology/approach The panel method was applied to aerodynamic analysis and was coupled with open-source FEM code within one computational process. Findings The numerical results proved the effectiveness of developed methodology. Practical implications Developed software can be used within the design process of a new aircraft. Originality/value This paper presents an original approach for advanced numerical analysis, as well as for multidisciplinary optimization of an aircraft. The presented results show possible applications.

Design of morphing wing with surface discontinuity

“…The package was designed in mid-nineties and has since been explored to compute aircraft aerodynamic characteristics including stability derivatives. [11][12][13][14] The package is reaching its maturity through constant development.…”

Structural sizing for the weight estimation of a very light aircraft wing

“…Although the current computational resources make it possible to conduct high-fidelity CFD modeling at a relatively low cost, methods based on potential theory are still in use due to their implementation simplicity and reduced processing time. 5 The other reason is that they are accurate enough for simulating low-speed aerodynamics and particularly in the case of small aircrafts. The aerodynamic loads acting on the wing are calculated by means of the VLM.…”

“…With the growing need to improve the performance of new aircraft concepts, numerical optimization have been widely used in aeronautical engineering, considering the different disciplines involved, namely aerodynamics, structures, propulsion, control, etc. [5][6][7] Modern aircraft development gives much attention to the wing design because of its role as the primary lifting surface. One of the fundamental requirements when designing a new aircraft is to reduce its structural weight.…”

Aerodynamic Shape Optimization of Aircraft Wings Using Panel Methods

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