NONDIMENSIONAL CALCULATION OF TURBULENT BOUNDARY-LAYER DEVELOPMENT IN TWO-DIMENSIONAL NOZZLES OF SUPERSONIC WIND TUNNELS

Abstract

The method developed by Maurice Tucker (Approximate Calculation of Turbulent Boundary Layer Development in Compressible Flow, NACA TN 2337, 1951) for calculating the growth of turbulent boundary layers in two-dimensional compressible flow has been adapted to the computation of a dimensionless boundary-layer parameter. Equations and calculational procedures are presented for correcting two-dimensional supersonic nozzles for boundary-layer growth using only one or two tables, depending on the geometry. The tables are supplied for the Mach number range fro 1.5 to 8.0. Agreement of calculated data with measured data and effect of Mach number distribution are shown.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1962
Accession Number
AD0270596

Entities

People

  • H. Maxwell
  • J. L. Jacocks

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Compressible Flow
  • Equations
  • Flow
  • Fluid Flow
  • Geometry
  • Government Procurement
  • Layers
  • Mach Number
  • Nozzles
  • Pressure Gradients
  • Supersonic Nozzles
  • Turbulent Boundary Layer
  • Two Dimensional
  • Viscous Flow
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Computational Fluid Dynamics (CFD)
  • Regression Analysis.

Technology Areas

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