SECOND ORDER BOUNDARY LAYER THEORY FOR TWO-DIMENSIONAL AND AXIALLY SYMMETRIC FLOW (Grenzschichttheorie Zweiter Ordnung fuer Ebene und Achsensymmetrische Hyperschallstroemung)

Abstract

It is shown that there is an interaction between pressure gradients normal and parallel to the surface in supersonic flows and that the effect of longitudinal curvature increases strongly with Mach number. The second order boundary layer equations and the matching conditions with the inviscid flow are discussed. As well as longitudinal curvature, transverse curvature and variations in stagnation pressure and enthalpy, are considered as second order effects. Integral relationships of the boundary layer equations (momentum, energy equation, etc.) are given. The effects are demonstrated by a numerical example of a laminar boundary layer profile and possibilities for an approximate solution of the equations are discussed.

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1969
Accession Number
AD0687808

Entities

People

  • J. C. Rotta

Organizations

  • Royal Aircraft Establishment

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Boundary Layer
  • Differential Equations
  • Energy
  • Equations
  • Flow
  • Flow Fields
  • Heat Transfer
  • Heat Transfer Coefficients
  • Hypersonic Flow
  • Inviscid Flow
  • Laminar Boundary Layer
  • Layers
  • Lepidoptera
  • Mach Number
  • Pressure Distribution
  • Pressure Gradients
  • Supersonic Flow

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers