국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	Unsteady Aerodynamic Model Tuning for Precise Flutter Prediction.
저자	Pak, Chan-gi
Keyword	AERODYNAMIC CHARACTERISTICS;; AERODYNAMIC COEFFICIENTS;; AEROELASTICITY;; DYNAMIC MODELS;; ESTIMATING;; FLIGHT TESTS;; FLUTTER ANALYSIS;; INFLUENCE COEFFICIENT;; MACH NUMBER;; PREDICTION ANALYSIS TECHNIQUES;; UNSTEADY AERODYNAMICS
URL	http://hdl.handle.net/2060/20110023913
보고서번호	NASA/TM-2011-215963
발행년도	2011
출처	NTRS (NASA Technical Report Server)
ABSTRACT	A simple method for an unsteady aerodynamic model tuning is proposed in this study. This method is based on the direct modification of the aerodynamic influence coefficient matrices. The aerostructures test wing 2 flight-test data is used to demonstrate the proposed model tuning method. The flutter speed margin computed using only the test validated structural dynamic model can be improved using the additional unsteady aerodynamic model tuning, and then the flutter speed margin requirement of 15 percent in military specifications can apply towards the test validated aeroelastic model. In this study, unsteady aerodynamic model tunings are performed at two time invariant flight conditions, at Mach numbers of 0.390 and 0.456. When the Mach number for the unsteady aerodynamic model tuning approaches to the measured fluttering Mach number, 0.502, at the flight altitude of 9,837 ft, the estimated flutter speed is approached to the measured flutter speed at this altitude. The minimum flutter speed difference between the estimated and measured flutter speed is -0.14 percent.