Calculation of Thicknesses of Laminar Boundary Layers in Axisymmetric Nozzles with Low-Density, Hypervelocity Flows,

Abstract

A new method for the estimation of boundarylayer thickness corrections to the contours of cooled axisymmetric nozzles for low-density, hypersonic flows is presented. Laminar flows of real gases in thermodynamic equilibrium with possible variation of specific heats, frozen flows, and boundary-layer thicknesses of the order of nozzle radii are considered. The derivation combines an appropriate integral momentum relation with an approximate friction law based on local similarity. Results of application of the method to several typical cases are shown to agree closely with experimental data. (Author)

Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1961
Accession Number
AD0267919

Entities

People

  • J. Leith Potter
  • J.a. Durand

Organizations

  • Arnold Engineering Development Complex

Tags

DTIC Thesaurus Topics

  • Axisymmetric
  • Boundaries
  • Boundary Layer
  • Experimental Data
  • Flow
  • Hypersonic Flow
  • Hypervelocity Flow
  • Laminar Boundary Layer
  • Laminar Flow
  • Layers
  • Low Density
  • Specific Heat
  • Thickness

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)
  • Ocean-Atmosphere Mesoscale Modeling, Data Assimilation, and Flux Boundary Layers

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers