HYPERSONIC FLOW FIELD ABOUT A BLUNT SLAB WING AT ANGLE OF ATTACK: PHASE I,
Abstract
This report describes an experimental research program to investigate the flow fields about blunt nosed wings and bodies at angle of attack. Phase I is an investigation of the inviscid two-dimensional flow field about a blunt nosed flat plate and a larger transverse cylinger-plate at a Mach number of 7.6 and angles of attack up to 40 degrees. By traversing the flow between the wing and the bow shock at various chordwise stations with a pitot probe, the streamline patterns and the flow property variations along them are established for each angle of attack. Also included are schlieren photographs of the shock wave shapes, estimates of the boundary layer thicknesses, and the results of a brief investigation to determine the feasibility or an experimental method of sonic line location. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1964
- Accession Number
- AD0615008
Entities
People
- Robert J. Polutchko
Organizations
- Massachusetts Institute of Technology