EXPLORATORY TESTS OF THE EFFECTS OF JET PLUMES ON THE FLOW OVER CONE-CYLINDER-FLARE BODIES.

Abstract

Schlieren photographs were taken of the flow over cone-cylinder-flare bodies to study the extent of boundary-layer separation due to the presence of rocket jet plumes. Tests were made of three cone-cylinder-flare configurations in the Langley 11-inch hypersonic tunnel at a Mach number of 9.65 and in the Langley Unitary Plan wind tunnel at a Mach number of 4.65 with two additional configurations. The stream Reynolds number varied from approximately 317,000 to 582,000 based on model length. The conical flares had half-angles of 7 or 13 degrees and contained one of two test nozzles with a design Mach number of 3.72 or 4.53.

Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1962
Accession Number
AD0270677

Entities

People

  • Davis H. Crawford
  • Ralph A. Flanga
  • William F. Hinson

Organizations

  • National Academy of Sciences

Tags

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Fluid Mechanics
  • Layers
  • Mach Number
  • Photographic Materials
  • Photographs
  • Photography
  • Reynolds Number
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Marine Hydrodynamics
  • Rocket Propulsion.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow