Effect of Sideslip on the Flow over a 65-deg Delta Wing

Abstract

Flow-visualization tests, surface-pressure measurements and balance tests were conducted on a model of a flat-plate 65-deg swept delta wing in a low-speed wind tunnel. The model was tested at a fixed angle of attack of 30 deg and at angles of sideslip up to 20 deg. The tests generated data that were used to study the effect of sideslip on the flow over the delta wing.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1999
Accession Number
ADA361146

Entities

People

  • Nicolaas G. Verhaagen

Organizations

  • Delft University of Technology

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Air Force Research Laboratories
  • Aircraft Equipment
  • Aircrafts
  • Boundary Layer
  • Boundary Layer Transition
  • Computational Fluid Dynamics
  • Delta Wings
  • Dynamic Pressure
  • Flow
  • Flow Visualization
  • Measurement
  • Pressure Distribution
  • Pressure Measurement
  • Research Facilities
  • Skin Friction
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Fluid Mechanics and Fluid Dynamics.