Analysis of Laminar Boundary Layers on Right Circular Cones at Angle of Attack, Including Streamline-Swallowing Effects

Abstract

A method has been developed for treating the three-dimensional compressible laminar boundary-layer equations for a right circular cone at angle of attack in supersonic and hypersonic flow. Swallowing by the boundary layer of the inviscid entropy layer (streamline swallowing) has been treated by means of a mass-flow balance between the inviscid and viscous flowfields. The boundary- layer equations between the inviscid and viscous flowfields. The boundary-layer equations were developed in a general Crocco-variables form. A finite- difference technique was formulated for solving the governing equations and treating the streamline-swallowing phenomenon. The resulting second-order difference equations are solved in an iteration scheme.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1972
Accession Number
AD0750130

Entities

People

  • Arloe W. Mayne Jr.

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Air Force
  • Axisymmetric Flow
  • Boundary Layer
  • Boundary Layer Flow
  • Bow Shock
  • Conical Bodies
  • Difference Equations
  • Differential Equations
  • Equations
  • Experimental Data
  • Geometry
  • Hypersonic Flow
  • Laminar Boundary Layer
  • Mach Number
  • Mass Flow
  • Partial Differential Equations
  • Three Dimensional

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers