Accession Number : AD0667375

Title :   DIFFUSER SIDE WALL ATTACHMENT DATA DYNAMIC MODEL - SUPERSONIC VELOCITY.

Descriptive Note : Memorandum rept.,

Corporate Author : MARYLAND UNIV COLLEGE PARK DEPT OF WIND TUNNEL OPERATIONS

Personal Author(s) : Bowers,Allen A.

Report Date : JUN 1961

Pagination or Media Count : 80

Abstract : The investigation was conducted at a simulated supersonic velocity equivalent to a Mach number of 1.20. The dynamic model was used to investigate the effects of changing configurations at a simulated supersonic velocity. The model was constructed so that the nozzle throat, the diffuser walls, and the diffuser angles and the diffuser wall setback could all be varied independently. The purpose of the investigation was to observe and record the flow attachment point for each configuration. As the flow passes through the nozzle throat and travels into the diffuser, it attaches itself to one of the diffuser walls. The attachment point was measured by placing a small probe into the flow perpendicular to the water surface and adjacent to the right diffuser wall. A colored dye solution was introduced to the flow through a probe that could be moved fore and aft parallel to the diffuser wall. When the dye trace indicated an area of stagnation this location was recorded as the attachment point. (Author)

Descriptors :   (*SUPERSONIC DIFFUSERS, SUPERSONIC CHARACTERISTICS), NOZZLE GAS FLOW, VELOCITY, WALLS, WIND TUNNEL MODELS, EXPERIMENTAL DATA, NOZZLE THROATS, AERODYNAMIC CONFIGURATIONS, FLOW VISUALIZATION, ATTACHMENT, STAGNATION POINT, FLUIDICS

Subject Categories : Aerodynamics
      Fluidics and Fluerics

Distribution Statement : APPROVED FOR PUBLIC RELEASE