Unsteady Aerodynamics.
Abstract
The Symposium identified the need for carefully conceived experimental unsteady flow data, particularly for both unseparated and separated two- and three-dimensional turbulent boundary layers. Detailed, accurate measurements of critical flow parameters was encouraged. It was agreed that linearized theories of unsteady inviscid flows provided a useful basis for many engineering applications, particularly in the early design stages of aircraft, but for more reliable calculations in the transonic and supersonic regimes the emphasis should be on development of non-linear numerical methods. Transonic numerical codes are increasingly efficient but their validity and accuracy needs assessment. Future calculations should include boundary layer effects even if no shock-wave interaction is included. The importance of Reynolds number on the dynamic stall was indicated. It was advised that serious consideration should be given to the development of a manual aeroelasticity of turbo-machines. An important factor in determining the characteristics of a rotor blade is the interaction of the blade with vortices shed by other blades. Research is required on the nature of this interaction and its effect on the dynamic stall of the blade. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 1978
- Accession Number
- ADA054028
Entities
Organizations
- AGARD