지원사업
학술연구/단체지원/교육 등 연구자 활동을 지속하도록 DBpia가 지원하고 있어요.
커뮤니티
연구자들이 자신의 연구와 전문성을 널리 알리고, 새로운 협력의 기회를 만들 수 있는 네트워킹 공간이에요.
논문 기본 정보
- 자료유형
- 학술대회자료
- 저자정보
- 발행연도
- 2012.5
- 수록면
- 71 - 77 (7page)
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초록· 키워드
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The flow field of helicopter is subjected to the influence of tip vortices that maintains its strength for several rotor revolutions. Each helical tip vortex induces the strong downwash on the rotor disk; the accuracy of the vortex capturing determines the prediction qualities of vortex interaction noise as well as the precision of the helicopter performance estimation. For the precise vortex capturing, it is a matter of common knowledge that the high order space differential scheme or the high density of grid system is effective. While the structured grid system can implement the high order scheme easier than the unstructured grid system, the inefficiency of the grid system occurs because the required number of grid around the vortex is very small relative to the total number of the background grid. In this paper, the adaptive wavelet method is presented as an efficient compromise way for the structured grid system. The adaptive wavelet uses the interpolating wavelet transformation including decomposition and threshold to construct an adaptive dataset to a solution. Then, fluxes are calculated only at the points within the adaptive dataset, which enhances the computational efficiency. As a practical application to demonstrate the usability of the wavelet method, the 2D airfoil vortex interaction problem is solved by the Euler solver with the adaptive wavelet equation. 4 stage Runge-Kutta for temporal integration and 5th order WENO scheme for inviscid fluxes are applied. As results, the wavelet method increases the calculation efficiency of WENO scheme(24% reduction of elapsed time than WENO scheme without wavelet method) while maintains its high accuracy for the low vortex diffusion.
목차
1. 서론
2. 수치해석기법
3. 해석결과
4. 결론
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UCI(KEPA) : I410-ECN-0101-2013-422-002847744