COMPUTATION OF THE LAMINAR COMPRESSIBLE BOUNDARY LAYER.

Abstract

First-and second-order boundary-layer theory are examined in detail for some specific flow cases of practical interest. These cases are for flows over blunt axisymmetric bodies in hypersonic high-altitude (or low density) flow where second-order boundary-layer quantities may become important. These cases consist of flow over a hyperboloid and a paraboloid both with free-stream Mach number infinity and flow over a sphere at free-stream Mach number 10. The method employed in finding the solutions is an implicit finite-difference scheme. It is found to exhibit both stability and accuracy in the examples computed. The method consists of starting near the stagnation-point of a blunt body and marching downstream along the body surface. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1964
Accession Number
AD0607573

Entities

People

  • Irmgard Flugge-lotz

Organizations

  • Stanford University

Tags

DTIC Thesaurus Topics

  • Altitude
  • Blunt Bodies
  • Bodies
  • Boundaries
  • Boundary Layer
  • Flow
  • Free Stream
  • High Altitude
  • Layers
  • Low Density
  • Mach Number
  • Stagnation Point

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.

Technology Areas

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