LAMINAR AND TURBULENT BOUNDARY LAYERS ON SLIGHTLY-BLUNTED CONES AT HYPERSONIC SPEEDS

Abstract

A momentum-integral method for calculating the boundary-layer growth on slightly-blunted cones has been given in a previous paper by the writer. The method, which was applied to cones with fully laminar flow, is extended in the present paper to turbulent flow. In addition: (1) transition data on cones at hypersonic speeds are examined to show the great effect of slight nose blunting on interpretation of the results, (2) agreement between measured and calculated cone drag coefficients for fully laminar flow is demonstrated, and (3) turbulent friction and boundary-layer thickness calculations are shown to agree with the limited amount of ballistics range data which are available.

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Document Details

Document Type
Technical Report
Publication Date
Mar 21, 1966
Accession Number
AD0632714

Entities

People

  • R. E. Wilson

Organizations

  • Naval Ordnance Laboratory

Tags

DTIC Thesaurus Topics

  • Boundary Layer
  • Boundary Layer Flow
  • Bow Shock
  • Coefficients
  • Fluid Dynamics
  • Integral Equations
  • Laminar Boundary Layer
  • Laminar Flow
  • Mach Number
  • Mass Flow
  • Munitions
  • Ordnance Laboratories
  • Reynolds Number
  • Shear Stresses
  • Skin Friction
  • Turbulent Boundary Layer
  • Turbulent Flow

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers