Boundary-Layer Transition on Cones Near Mach One in an Aeroballistic Range

Abstract

The feasibility of determining Reynolds numbers of boundary layer transition on sharp, 10-deg, semiangle cones at slightly supersonic free-stream Mach numbers, 1.04 = or < M = or < 1.44, in an aeroballistic range has been demonstrated. Some problems relating to the experimental technique are discussed, and the data are compared with results for higher Mach numbers. Possibly important differences between transonic wind tunnels and the aeroballistic range are pointee out in connection with a warning about comparing transition data from different facilities.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1975
Accession Number
ADA003493

Entities

People

  • J. Leith Potter

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms
  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Air Force
  • Boundaries
  • Boundary Layer
  • Boundary Layer Transition
  • Bow Shock
  • Flow
  • Flow Fields
  • Fluid Dynamics
  • Free Stream
  • Jet Propulsion
  • Layers
  • Mach Number
  • Measurement
  • Reynolds Number
  • Tennessee
  • Transonic Wind Tunnels
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Fluid Dynamics.
  • ballistics.

Technology Areas

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