BOUNDARY LAYER TRANSITION AT SUPERSONIC SPEEDS THREE DIMENSIONAL ROUGHNESS EFFECTS (SPHERES)

Abstract

Experiments carried out in the 12-inch supersonic wind tunnel to investigate the effect of three dimensional roughness elements (spheres) on boundary-layer transition on a 10-degree (apex angle) cone without heat transfer are described. The local Mach number for these tests was 2.71. The data show clearly that the minimum (effective) size of trip required to bring transition to its lowest Reynolds number varies power of the distance from the apex of the cone to the trip. Use of available data at other Mach numbers indicates that the Mach number influence for effective tripping is taken into account by a simple expression. Some remarks concerning the roughness variation for transition on a blunt body are made. Finally, a general criterion is introduced which gives insight to the transition phenomenon and anticipates effects of external and internal disturbances, Mach number transfer.

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Document Details

Document Type
Technical Report
Publication Date
Aug 15, 1961
Accession Number
AD0265237

Entities

People

  • C. B. Blumer
  • E. R. Van Driest

Tags

Communities of Interest

  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Air Force
  • Blunt Bodies
  • Boundary Layer
  • Boundary Layer Flow
  • Boundary Layer Transition
  • Computational Fluid Dynamics
  • Fluid Dynamics
  • Fluid Mechanics
  • Laminar Boundary Layer
  • Mach Number
  • Reynolds Number
  • Schematic Diagrams
  • Scientific Research
  • Supersonic Wind Tunnels
  • Three Dimensional
  • Turbulent Flow
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

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