FLIGHT FLUTTER RESULTS FOR FLAT RECTANGULAR PANELS
Abstract
Panel-flutter data obtained from several different aircraft during supersonic flight are presented and compared with a previously established flutter boundary based on results from windtunnel tests. The flight data were obtained for rectangular panels alined with the flow and for rectangular panels swept at 52 degrees. Some results of a flutter analysis of swept, flat, rectangular panels are presented and used to compare the flight results with the flutter boundary for alined panels. The flow direction was shown to have an appreciable effect on the flutter of swept rectangul r panels. The results for panels alined with the flow direction were found to be in satisfactory agreement with the flutter boundary established by wind-tunnel tests. Simple changes in panel geometry were found effective in eliminating flutter. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1962
- Accession Number
- AD0272127
Entities
People
- Eldon E. Kordes
- Richard B. Noll
Organizations
- National Aeronautics and Space Administration