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The coupled time-integration method with a staggered algorithm based on computational structural dynamics (CSD), finite element method (FEM) and computational fluid dynamics (CFD) has been developed in order to demonstrate physical vibration phenomena due to dynamic aeroelastic excitations. Virtual flutter tests for the spanwise curved wing model have been effectively conducted using the present advanced computational method with high speed parallel processing technique. In addition, the present system can simultaneously give a recorded data file to generate virtual animation for the flutter safety test. The results for virtual flutter test are compared with the experimental data of wind tunnel test. It is shown from the results that the effect of spanwise curvature have a tendency to decrease the flutter dynamic pressure for the same flight condition.攀†책임저자;정회원, 국립경상대학교 기계항공공학부 및 항공기부품기술연구소E-mail : dhk@gsnu.ac.krTel : (055) 751-6125, Fax : (055) 755-2081* 정회원, 국립경상대학교 대학원 기계항공공학부