Comparison of Numerical Results and Measured Data for Smooth and Indented Nosetips,

Abstract

Numerical calculations, using an unsteady implicit numerical algorithm which solves either the inviscid or the thin-layer Navier-Stokes equations, were performed for smooth and severely indented nosetips at hypersonic speed and zero angle of attack. The computed results of inviscid and laminar flowfield are compared to wind tunnel measured data for surface pressure, shock location, heat transfer and density distribution in the shock layer. Good agreements between the calculated and measured flowfield are obtained for smooth nosetip without flow separation. Difficulties in the simulation of severely indented nosetips with large separation bubble or sharp corner are discussed. (Author)

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Document Details

Document Type
Technical Report
Publication Date
May 14, 1981
Accession Number
ADA111794

Entities

People

  • Tsuying Hsieh

Organizations

  • Naval Ordnance Laboratory

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Coefficients
  • Computational Fluid Dynamics
  • Computer Programs
  • Equations
  • Flow
  • Fluid Dynamics
  • Fluid Flow
  • Heat Transfer
  • Laminar Flow
  • Layers
  • Molecular Dynamics
  • Navier Stokes Equations
  • Pressure Distribution
  • Simulations
  • Turbulent Flow
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Computational Fluid Dynamics (CFD)
  • Fluid Dynamics.

Technology Areas

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