Review of Requirements and Status of Simulation and Scaling of Transonic, Viscous Flows
Abstract
The elements of transonic, viscous-flow simulation are reviewed, documented, and briefly evaluated in the light of newer results from research in this field. Not only the case of wing flows at low angles of attack, but also the problems arising with wings and fuselages or missiles at higher angles are discussed. Criteria to be satisfied in scale-model testing and means for doing that are the principal topics covered. This includes the experimental techniques for simulating shock wave-boundary layer interaction, obtaining full-scale shock location and overall aerodynamic coefficients, and the precautions associated with boundary layer tripping in various types of testing. Vortical flows receive attention, and the requirement for assessing Reynolds number effects is emphasized. The review brings together information from diverse sources that wind tunnel test planners need in further improving experimental results and which is also critical in extrapolating those data to full-scale flight conditions. The subject of this report will continue to be of concern even though capabilities in computational fluid dynamics are rapidly growing, and the recently dedicated National Transonic Facility at the Langley Research Center will provide much increased test Reynolds numbers.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1984
- Accession Number
- ADA146357
Entities
People
- J. L. Potter
Organizations
- Arnold Engineering Development Complex