STUDY OF THE EFFECTS PRODUCED BY ASYMMETRICAL NOZZLE ENTRANCE GEOMETRIES ON THE DOWNSTREAM SUPERSONIC FLOW.

Abstract

Flow through a two-dimensional nozzle with asymmetrical entrance regions was studied using schlieren photographs and lateral-thrust versus chamber-pressure profiles. Lateral thrust was produced by asymmetrical flow separation and its magnitude was as much as twelve percent of the maximum axial thrust produced by the nozzle. Asymmetrical separation occurred at low pressures for both symmetrical and asymmetrical entrances, but the lateral-thrust profile was inconsistent for the symmetrical entrance. Inserts were used to obtain seven asymmetrical nozzle entrances which all affected the supersonic flow. (Author)

Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1968
Accession Number
AD0832522

Entities

People

  • Richard L. Thompson

Organizations

  • Air Force Institute of Technology

Tags

DTIC Thesaurus Topics

  • Flow
  • Flow Separation
  • Geometry
  • Mathematics
  • Photographic Materials
  • Photographs
  • Photography
  • Plane Geometry
  • Sizes (Dimensions)
  • Supersonic Flow
  • Two Dimensional

Readers

  • Combustion and Flow Dynamics.
  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow