EFFECT OF ROUGHNESS ON TRANSITION IN SUPERSONIC FLOW

Abstract

Experiments were carried out in the 12-in. 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. 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 as the one-fourth 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 the simple expression Reynold's number based on displacement thickness = 1050(1 + 1/2(gamma - 1) Mach number based on displacement thickness squared) (roughness element height/boundary layer displacement thickness)-2. (Author)

Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1960
Accession Number
AD0262485

Entities

People

  • C.b. Blumer
  • E.r. Van Driest

Organizations

  • AGARD

Tags

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Boundary Layer Transition
  • Displacement
  • Heat Transfer
  • Layers
  • Mach Number
  • Reynolds Number
  • Roughness
  • Supersonic Flow
  • Supersonic Wind Tunnels
  • Thickness
  • Three Dimensional
  • Transitions
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.
  • Mathematics or Statistics
  • Structural Dynamics.

Technology Areas

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