INVESTIGATION OF THE EFFECTS OF AIR INJECTION UPON THE HYPERSONIC LAMINAR BOUNDARY LAYER

Abstract

An experimental study was conducted to obtain boundary-layer pitot pressure profile data on a sharp and a blunt leading edge rectangular plate and a sharp leading edge delta wing at Mach 6, 8, and 10. Effects of Reynolds number, angle of attack, and mass injection were studied. Selected results are presented to illustrate the effect of air injection upon the sharp rectangular plate boundary layer at Mach 8 and zero angle of attack.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1966
Accession Number
AD0480606

Entities

People

  • A. D. Ray
  • R. L. Palko

Organizations

  • Arnold Engineering Development Complex

Tags

DTIC Thesaurus Topics

  • Abstracts
  • Air Force
  • Boundaries
  • Boundary Layer
  • Flow
  • Fluid Dynamics
  • Fluid Mechanics
  • Free Stream
  • Government (Foreign)
  • Government Procurement
  • Governments
  • Instrumentation
  • Laminar Boundary Layer
  • Layers
  • Reynolds Number
  • Stagnation Pressure
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

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