국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	Application of Approximate Unsteady Aerodynamics for Flutter Analysis.
저자	Pak, Chan-gi;; Li, Wesley W.
Keyword	AERODYNAMIC COEFFICIENTS;; AERODYNAMICS;; APPROXIMATION;; BODY-WING CONFIGURATIONS;; FLUTTER;; FLUTTER ANALYSIS;; MULTIDISCIPLINARY DESIGN OPTIMIZATION;; PREDICTION ANALYSIS TECHNIQUES;; RATIONAL FUNCTIONS;; UNSTEADY AERODYNAMICS;; WINGS
URL	http://hdl.handle.net/2060/20100039468
보고서번호	NASA/TM-2010-216387
발행년도	2010
출처	NTRS (NASA Technical Report Server)
ABSTRACT	A technique for approximating the modal aerodynamic influence coefficient (AIC) matrices by using basis functions has been developed. A process for using the resulting approximated modal AIC matrix in aeroelastic analysis has also been developed. The method requires the unsteady aerodynamics in frequency domain, and this methodology can be applied to the unsteady subsonic, transonic, and supersonic aerodynamics. The flutter solution can be found by the classic methods, such as rational function approximation, k, p-k, p, root locus et cetera. The unsteady aeroelastic analysis using unsteady subsonic aerodynamic approximation is demonstrated herein. The technique presented is shown to offer consistent flutter speed prediction on an aerostructures test wing (ATW) 2 and a hybrid wing body (HWB) type of vehicle configuration with negligible loss in precision. This method computes AICs that are functions of the changing parameters being studied and are generated within minutes of CPU time instead of hours. These results may have practical application in parametric flutter analyses as well as more efficient multidisciplinary design and optimization studies.