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논문 기본 정보

자료유형
학술저널
저자정보
Alexander Kuzmin (St. Petersburg State University)
저널정보
한국항공우주학회 International Journal of Aeronautical and Space Sciences International Journal of Aeronautical and Space Sciences Volume.15 Number.3
발행연도
2014.9
수록면
232 - 240 (9page)

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초록· 키워드

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Transonic flow past a NASA SC(2)-0710 airfoil with deployments of a spoiler up to 6° was studied numerically. We consider angles of attack from -0.6° to 0.6° and free-stream Mach numbers from 0.81 to 0.86. Solutions of the unsteady Reynoldsaveraged Navier-Stokes equations were obtained with a finite-volume solver using several turbulence models. Both stationary and time-dependent deployments of the spoiler were examined. The study revealed the existence of narrow bands of the Mach number, angle of attack, and spoiler deflection angle, in which the flow was extremely sensitive to small perturbations. Simulations of 3D flow past a swept wing confirmed the flow sensitivity to small perturbations of boundary conditions.

목차

Abstract
1. Introduction
2. Formulation of the problem
3. Numerical method
4. Lift coefficient versus M for the airfoil (1)(no spoiler deployment)
5. Lift coefficient behavior for airfoil (1)-(3)at the spoiler deployment angle of 3°
6. Aerodynamic coefficient behavior at a spoiler deployment angle of 6°
7. Miscellania
8. 3D wings
9. Conclusions
References

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