서지주요정보
오일러 방정식을 이용한 비행체 날개의 천음속 플러터 해석 = Transonic flutter analysis for airfoils and wings using euler equations
서명 / 저자 오일러 방정식을 이용한 비행체 날개의 천음속 플러터 해석 = Transonic flutter analysis for airfoils and wings using euler equations / 양성모.
저자명 양성모 ; Yang, Sung-Mo
발행사항 [대전 : 한국과학기술원, 1996].
Online Access 원문보기 원문인쇄

소장정보

등록번호

8006213

소장위치/청구기호

학술문화관(문화관) 보존서고

DAE 96002

SMS전송

도서상태

이용가능

대출가능

반납예정일

초록정보

In this study the computer programs for transonic flutter analysis have been developed which can be applied to two-dimensional airfoils and three-dimensional wings. Using the developed Euler codes, the transonic flutter analyses have been performed for two-dimensional typical section model with a flap degree-of-freedom and three- dimensional isotropic and composite wings. Time dependant compressible Euler equations, which are used to calculate steady and unsteady aerodynamics and generalized aerodynamic forces, are solved using a central-differenced finite volume scheme and two kinds of time integration methods(4th order Runge-Kutta method and diagonalized alternating direction implicit method). The dynamic grid generation procedure which is applied to generate instantaneous grid of a moving body at every time step during unsteady motion is carried out using the spring analogy method and the linear interpolation method. The transient pulse technique has been introduced to obtain generailzed aerodynamic forces which are necessary to calculate flutter points by the U-g method. The composite wing structures are modeled as a laminated composite plate. The generalized mass and stiffness matrices are generated using the finite element method based on the first-order shear deformable theory. The surface spline method is employed to interconnect the structural nodal and aerodynamic grid points. The flutter boundary is predicted using both the coupled time-integration method and the U-g method. To validate the developed flutter analysis codes, many numerical examinations have been performed for steady and unsteady aerodynamics, generalized aerodynamics, and flutter results. The present results have been compared with experimental and other numerical results and are proved to have a good agreement with the previous results. The present codes have been applied to the two- dimensional typical section model with a flap degree-of-freedom and three-dimensional isotropic and composite wings. In case of the flap degree-of-freedom typical section model, the instability of the flap motion increases as Mach number and the initial flap angle increase and/or the structural damping coefficient decreases. In case of the three dimensional isotropic wing, which is a rectangular wing with a biconvex airfoil, the computed flutter dynamic pressures are very accurate compared with experiment and the DLM results. As the airfoil thickness of the wing(the strength of steady shock wave) increases, the flutter dynamic pressure increases both in the transonic and sub- supersonic flow regime. In case of the composite wing, the characteristics of flutter boundary in the transonic flow region are very different from those in subsonic flow regime because of aerodynamic nonlinearities.

서지기타정보

서지기타정보
청구기호 {DAE 96002
형태사항 x, 135 p. : 삽도 ; 26 cm
언어 한국어
일반주기 저자명의 영문표기 : Sung-Mo Yang
지도교수의 한글표기 : 이인
지도교수의 영문표기 : In Lee
학위논문 학위논문(박사) - 한국과학기술원 : 항공우주공학과,
서지주기 참고문헌 : p. 126-135
주제 공탄성
천음속 플러터
유한체적법
오일러방정식
정상 및 비정상공기력
일반력
유한요소법
과도충격법
표면보간법
연계적분법
U-g
플랩단면모델
등방성 및 복합재 날개
Aeroelasticiy
Transonic Flutter
CFD
Euler Equation
Steady and Unsteady Aerodynamics
Generalized Aerodynamic Forces
FEM
Transient Pulse Method
Surface Spline Method
Coupled Time-Integration Method
U-G
Flap Typical Section
Isotropic and Composite Wing
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