Investigation of Boundary Layer Shock Interaction at Transonic Speed.
Abstract
The report describes the design of a facility for studying experimentally the flow field at transonic speed above and near a wing profile, with the objective of determining the supersonic expansion wave-shock configuration. A two-dimensional flow field is considered and a rectangular wing profile, folded into an axially symmetric ring, is used as a model. Test Reynolds numbers are to about 100 million. Modification of the flow field is introduced with (a) variable plenum chamber pressure around the slotted-porous tunnel wall and (b) a mechanism for changing porosity distribution on the slotted wall. Preliminary tests to determine flow uniformity and influence of the variable porosity mechanism are reported.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1974
- Accession Number
- ADA004811
Entities
People
- Sergio Panunzio
Organizations
- New York University