Analysis of Nosetip Boundary Layer Transition Mechanisms

Abstract

Linear stability theory is being used to investigate the mechanisms which lead to boundary layer transition on re-entry vehicle nosetips. Specific efforts are aimed at determining the effects of various parameters including surface roughness, ablation, wall cooling, local Mach numbers, pressure gradient, and axisymmetric geometry on transition. Roughness is simulated by means of the 'turbulent sublayer' model which has been extended to compressible flow. Results indicate that both roughness and ablation strongly reduce the transition Reynolds number. A series of parametric stability solutions has been calculated for non-zero pressure gradient cases. Thus far, rough-wall solutions have been completed only near the stagnation point where the boundary layer is still stable to all disturbances.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1975
Accession Number
ADA017585

Entities

People

  • Charles L. Merkle
  • Denny R. S. Ko
  • Toshi Kubota
  • Walter J. Grabowski

Tags

Communities of Interest

  • Energy and Power Technologies
  • Materials and Manufacturing Processes
  • Space

DTIC Thesaurus Topics

  • Boundary Layer
  • Boundary Layer Flow
  • Boundary Layer Transition
  • Computational Fluid Dynamics
  • Differential Equations
  • Energy
  • Energy Transfer
  • Equations Of Motion
  • Fluid Dynamics
  • Fluid Flow
  • Free Flight
  • Geometry
  • Heat Transfer
  • Jet Propulsion
  • Three Dimensional
  • Turbulent Mixing
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.