In wind tunnel flutter test, the matching degree between scaled model and prototype would directly affect the reliability of test results. It is difficult to achieve completely dynamic similarity for some material or technological constrains, and only lower order modes can be accurately simulated to construct a compromised model. Theoretical support would be necessary to answer the question of how to define the order of modes simulated in order to guarantee data validity of wind tunnel flutter test. An analytical study of a sweepback wing was undertaken to estimate the main mode orders needed for accurate flutter prediction by comparing generalized aerodynamic stiffness coefficient, unsteady aerodynamic force and flutter results. The results show that the aerodynamic stiffness coefficient with expression of mode shape could be taken as a quick criterion for mode selection in flutter model design and analysis, and the research could be used to effective control the order of the model and improve model design efficiency.
ZHAO Ling
,
JI Chen
,
LIU Zi-Qiang
. Analysis and Judgment of Flutter Influence Mode of High speed Wing Model[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 0
: 0
-0
.
DOI: 10.7527/S1000-6893.2014.0252
[1]管德.飞机气动弹性力学手册[M] .北京: 航空工业出版社, 1994: 215-217.
[2]Guan De.Aircraft Aeroelasticity Handbook [M]. Beijing: Aviation Industry Press, 1994: 215-217. (in Chinese)
[3]Ron Busan.Flutter Model Technology[R]. WL–TR–97–3074, 1997
[4]D D.Liu, D.Sarhaddi, F.M. Piolenc. Flutter Prevention Handbook: A Preliminary Collection[R]. WL–TR–96–3111, 1996
[5]A L Head.. 颤振设计原理-美国关于气动弹性问题的专家会议资料[J]. 国际航空杂志社, 1960, (10):69-77
[6]A L Head..Flutter Design Principle[J]. International Aviation, 1960(10): 69-77. (in Chinese)
[7]John F.McCarthy, JR. Gifford W. Asher John S. Pricce, JR. et al. Threedimensional Supersonic Flutter Model Test near Mach Number 1.5 [R]. WADC TECHNICAL REPORT 54-113, Massachusetts Institute of Technolo-gy, December 1955
[8]Lou S.Young. Transonic flutter investigation of models of proposed horizontal tails for the X-15 airplane[R].NASA TM X-442, Washington: National Aeronautics and Space Administration, February 1961
[9]Perry W.Hanson. Aerodynamic Effects of Some Confi-guration Variables o at Mach Numbers from 0.7 to 6.86[R]. NASA TN D-984, Washington: National Aero-nautics and Space Administration, February 1961
[10]William T.Lauten, Gilbert M. Levey, William O. Armstrong. Investigation of an all-movable control surface at a mach number of 6.86 for possible flut-ter[R].NACA RM L58B27, Washington: National Advi-sory Committee for Aeronautics, May 1958
[11]陈桂彬, 邹从青, 杨超.气动弹性设计基础[M] .北京: 北京航空航天大学出版社, 2004: 65-89.
[12]Chen Guibing, Zou Congqing, Yang Chao.Aeroelastic Design Foundation [M]. Beijing: Beijing University of Aeronautics and Astronautics Press, 2004:81-82. (in Chinese)
[13]J.P. Giesing, T.P. Kalman, W.P. Rodden. Subsonic Unsteady Aerodynamics for General Configurations[C], AIAA paper No. 72-26, San Diego, California: AIAA 10th Aerospace Sciences Meeting, 1972
[14]ATLEE M.Cunningham, JR. The Application of General Aerodynamic Lifting Surface Elements to Problems in Unsteady Transonic Flow[R].NASA CR-112264, 1973
[15]Milton D.Van Dyke. A Study of Second-Order Supersonic Flow Theory[R]. NACA TN 2200, Washington: California Institute of Technology, January 1951
[16]Jack J McNamara, Andrew R Crowell..Approximate Modeling of Unsteady Aerodynamics for Hypersonic Aeroelasticity [J].Journal of Aircraft, 2010, 47(6)
[17]杨炳渊, 宋伟力.应用当地流活塞理论的大攻角升力面颤振气动力表达式[J].上海力学, 1999, 20(3)
[18]Yang Binyuan, Song Weili.Expressions about Aerody-namic Forces of Flutter for Wing with High Angle of Attack by Local Flow Piston Theory[J]. Journal of Shanghai Mechanics, 1999, 20(3). (in Chinese)
[19]E.H.道尔.气动弹性力学现代教程[M], 陈文俊, 尹传家, 译.北京: 宇航出版社, 1991:67-69
[20]E.H. Dowell. Aeroelasticity Modern Tutorial [M]. Chen Wenjun, Yin Chuanjia, translated. Beijing: astronautic publishing house, 1991: 67-69. (in Chinese)