FLOW INVESTIGATION ABOUT A FIN PLATE MODEL AT A MACH NUMBER OF 11.26.
Abstract
The purpose of the investigation was to study the flow fields at M = 11 about a hemicylindrically blunted flat plate and four interchangeable fins which were attached to the plate. Two of the fins had hemicylindrical leading edges; one fin's leading edge was unswept while the other had a 45 degree sweep. The remaining two fins had sharp leading edges with one unswept and the other swept 45 degrees. The plate was varied in angle of attack from compression 10 degrees to expansion 10 degrees while the fins' yaw angle was varied from 0 degrees to 10 degrees. Five methods were utilized in the work. Static pressures were measured on the plate surface. Silicone oil flow studies were made on the fin and plate surfaces. A liquid flow visualization mixture was employed on the model surface to help distinguish the direction of flow, the separation areas, and reattachment regions. A vapor screen technique was utilized to help define the plate and fin shock locations and shapes. An equation was found for the variation of the shock shape of the hemicylindrical blunted plate from M = 3 to M = 20. The equation is based on the blast wave analogy. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1967
- Accession Number
- AD0661548
Entities
People
- John P. Thomas
Organizations
- Air Force Research Laboratory