Analytical and Experimental Investigations of Delta Wings in Incompressible Flow

Abstract

The theoretical analysis of delta wings in incompressible flow is created by a numerical lifting-surface theory based upon a velocity potential formulation. This theory has been expanded to include spanwise velocity effects and the leading-edge departion associated with delta wings. The numerical technique has made use of both fixed and free wakes. In the fixed-wake model, the analytical results of Brown and Michael have been used to position the leading-edge vortex. In the more refined free-wake model, the leading edge separation was modeled as a discrete number of vortices attached to the leading- edge, which are allowed to align themselves with streamlines. Experimental research included wind tunnel tests to determine the vortex location, vortex burst location, and upper surface pressure distribution on a delta wing, AR = 2, in an oscillatory airstream.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1976
Accession Number
ADA030883

Entities

People

  • Balusu M. Rao
  • James K. Nathman

Organizations

  • Texas A&M University

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircrafts
  • Computational Fluid Dynamics
  • Coordinate Systems
  • Equations
  • Flow Visualization
  • Geometry
  • Grids
  • Incompressible Flow
  • Measurement
  • Military Research
  • Pressure Distribution
  • Pressure Measurement
  • Reynolds Number
  • Steady Flow
  • Turbulent Mixing
  • Unsteady Flow
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Mechanics and Fluid Dynamics.