Nonlinear Reduced Order Modeling of Limit Cycle Oscillations of Aircraft Wings
Abstract
This report documents the result of an STTR Phase I on the investigation in the use of a frequency-domain proper orthogonal decomposition (POD) / Reduced Order Modeling (ROM) procedure in conjunction with a harmonic balance nonlinear scheme for the prediction and analysis of limit cycle oscillations (LCO) of aircraft wings/airfoils in transonic flow regimes. A significant milestone has been reached in the phase I work. With four related cases studied in LCO and flutter, the result is that our frequency-domain method producing highly accurate solutions over a wide ranges of frequencies is potentially two orders of magnitude faster than conventional time-marching methods for determining LCO and flutter. Further, the nonlinear solutions of LCO using harmonic balance scheme in frequency domain could lead to a much better understanding of LCO physics. Its adopted Eigen-mode solution methodology on the other hand should render it readily acceptable by the industry practice. Finally, STTR Phase II plan is presented in detail. Commercialization strategy of the would-be production-ready software is also discussed.
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 28, 2000
- Accession Number
- ADA384971
Entities
People
- D. D. Liu
- E. H. Dowell
- K. C. Hall
- P. C. Chen