AN EXPERIMENTAL INVESTIGATION OF THE AERODYNAMIC CHARACTERISTICS OF SLENDER HYPERSONIC VEHICLES AT HIGH ANGLES OF ATTACK

Abstract

Pressure, heat transfer, force, flow field surveys and flow visualization measurements on an inclined cone were obtained in a wind tunnel at a nominal Mach number of 6. Force measurements were also obtained for a 2/3 power law body and two ducted-cone configurations.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
May 01, 1968
Accession Number
AD0832027

Entities

People

  • Lionel Pasiuk
  • Robert H. Feldhuhn

Organizations

  • Naval Ordnance Laboratory

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Boundary Layer
  • Differential Equations
  • Flow
  • Flow Fields
  • Flow Visualization
  • Fluid Dynamics
  • Fluid Mechanics
  • Heat Transfer
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Pressure Measurement
  • Recording Systems
  • Temperature Gradients
  • Test Facilities
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Fluid Dynamics.

Technology Areas

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