THEORETICAL AND EXPERIMENTAL INVESTIGATION OF BOUNDARY LAYERS IN LOW DENSITY HYPERSONIC AXISYMMETRIC NOZZLES

Abstract

The viscous flow region in low density hypersonic axisymmetric nozzles was investigated both theoretically and experimentally. Nonsimilar solutions were obtained for the internal laminar boundary layer equations which include second-order transverse curvature terms. These solutions were obtained on a CDC 1604 digital computer. Four existing low density axisymmetric nozzles were considered. Numerical solutions were obtained for these nozzles using various plenum chamber conditions and wall temperature distributions. The plenum chamber conditions used in the numerical solutions for these nozzles produced a test section Mach number range of about 3.0 to 18.0 and a test section Reynolds number per foot range of about 1000 to 15,000. Some results of the numerical solutions are compared with experimental measurements of pitot pressure, relative heat flux, and nozzle wall heat transfer coefficients. In all comparisons the numerical solutions appear to be consistent with the experimental data.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1968
Accession Number
AD0674597

Entities

People

  • David L. Whitfield

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Equations
  • Experimental Data
  • Fluid Dynamics
  • Geometry
  • Heat Flux
  • Heat Transfer
  • Heat Transfer Coefficients
  • Laminar Boundary Layer
  • Low Density
  • Mach Number
  • Mathematical Analysis
  • Measurement
  • Pressure Distribution
  • Pressure Measurement
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.

Technology Areas

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