NOL Hypervelocity Wind Tunnel Report No. III: Theoretical Analysis of the Boundary Layer in the Nozzle,

Abstract

The equations used to calculate the boundary layer properties for use in the design of the Mach 10, 15, and 20 axisymmetric nozzles of the hypervelocity wind tunnel at NOL are derived. One equation is the integral moment-of-momentum differential equation for the boundary layer velocity profile shape parameter; the form of the equation is valid for a real gas. This equation is used with an axisymmetric integral momentum equation that is valid for thick as well as for thin boundary layers to calculate the total thickness and the displacement effect of the boundary layer. (Author)

Document Details

Document Type
Technical Report
Publication Date
Feb 26, 1971
Accession Number
AD0722346

Entities

People

  • Neal Tetervin

Organizations

  • Naval Ordnance Laboratory

Tags

DTIC Thesaurus Topics

  • Axisymmetric
  • Boundaries
  • Boundary Layer
  • Differential Equations
  • Displacement
  • Equations
  • Integrals
  • Layers
  • Mathematics
  • Momentum
  • Physical Properties
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.

Technology Areas

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