Schlieren Investigation of the Flow Phenomena About a Two-Dimensional Circular Cylinder in a Hypersonic Flow
Abstract
An experimental investigation is described of the fluid flow phenomena about a two-dimensional circular cylinder in a hypersonic stream. The data presented was accumulated solely through the use of the Schlieren technique of flow visualization. The primary purpose of the investigation was to document the variation of the flow pattern with respect to flow parameters and models employed. Data concerning stagnation point shock layer thickness, bow shock wave shape, secondary shock wave shape, initial viscous wake growth, shear layer surrounding the base flow region, and intrinsic properties of the models and facility used are presented and discussed. All tests were conducted at a nominal free stream Mach Number of 14, while the free stream Reynolds Number was varied from 3,200 to 64,400. Reynolds Number variation was achieved by holding total temperature constant, ranging total pressure from 800 to 2000 psia, and changing model diameters from 1/8 to 3/4 inch.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1964
- Accession Number
- AD0610509
Entities
People
- H. Oguro
- K. H. Token
Organizations
- University of Cincinnati