Development of variable-fidelity based selective design and flow analysis methods for practical aerodynamic design optimization실용적인 공력 최적설계를 위한 다신뢰도 기반 선택적 설계기법 및 공력 해석기법 개발

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There have been many attempts to apply computational design methods to engineering problems in industry. However, solving an engeering design problem requires very high computational costs, even when applying computational analysis with state-of-the-art parallel computing. The main objective of the current study is to develop an efficient design methodology to reduce the required costs for both finding an optimal design solution and the computational flow analysis for the function evaluation. In this thesis, efficient design method and flow analysis are considered. Efficient global optimization starts with a small number of initial samples to construct a response surface, and additional number of samples are required during a design process. Variable-fidelity (VF) flow analysis uses both high-fidelity (HF) and low-fidelity (LF) flow analyses to evaluate aerodynamic function values according to design variables. To improve their efficiencies, three methodologies are introduced in the current study. First, dynamic fidelity indicators (DFIs) are developed to estimate necessary fidelity of the flow analysis for the additional sample points, and a corresponding selective VF design method is developed. Second, a tightly coupled Euler/panel method is used for HF flow analysis. It reduces the computational cost by decreasing domain size of computational fluid dynamics by using panel method. Third, a nonlinear vortex lattice method (NVLM) is developed for LF flow analysis. The NVLM with table look-up can simulate nonlinear aerodynamic characteristics, such as transonic and viscous flows, which classical VLM cannot simulate. To accurately calcualte the effective angle of attack for table look-up, an equivalent lattice approach is developed. Finally, a VF aerodynamic design composed of the selective VF design method, tightly coupled Euler/panel method, and the NVLM is developed. It is applied to the design problem of reducing the drag force of a wing in transonic flow. As a result, the design optimization four times faster than the conventional design method using only single-fidelity flow analysis can be achieved. Design efficiency can be further improved by using an LF-based response surface and by fine-tuning threshold parameters in the DFIs.
Advisors
Lee, Duck Jooresearcher이덕주researcher
Description
한국과학기술원 :항공우주공학과,
Publisher
한국과학기술원
Issue Date
2018
Identifier
325007
Language
eng
Description

학위논문(박사) - 한국과학기술원 : 항공우주공학과, 2018.2,[vii, 113 p. :]

Keywords

Selective variable-fidelity design method▼avariable-fidelity kriging model▼adynamic fidelity indicator▼atightly coupled euler/panel method▼anonlinear vortex lattice method▼atable look-up▼aequivalent lattice approach▼avariable fidelity-based design optimization framework; 선택적 다신뢰도 설계 방법▼a다신뢰도 크리깅 모델▼a동적 해석 신뢰도 지시자▼a밀접 오일/패널 결합 방법▼a비선형 와류격자법▼a표검색법▼a등가 격자법▼a다신뢰도 기반 최적설계 프레임워크

URI
http://hdl.handle.net/10203/265419
Link
http://library.kaist.ac.kr/search/detail/view.do?bibCtrlNo=734454&flag=dissertation
Appears in Collection
AE-Theses_Ph.D.(박사논문)
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