Leading-Edge Separation from a Slender Rolling Wing-Body Combination.

Abstract

A vortex-sheet model of the leading-edge separation is used to study the flow about a slender wing-body combination in steady rolling motion at zero incidence. The equations which model the flow are derived and the numerical method to solve these equations is described. The results presented concentrate on those values of the parameters for which comparison may be made with the experimental results of Harvey for a rolling delta wing. Results obtained using simplified flow models are also described. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1980
Accession Number
ADA093971

Entities

People

  • I. P. Jones

Organizations

  • Royal Aircraft Establishment

Tags

DTIC Thesaurus Topics

  • Aircrafts
  • Boundary Layer
  • Coordinate Systems
  • Cross Flow
  • Delta Wings
  • Differential Equations
  • Equations
  • Flow Fields
  • Free Stream
  • Leading Edges
  • Measurement
  • Potential Flow
  • Pressure Distribution
  • Pressure Measurement
  • Stratified Fluids
  • Surface Properties
  • Turbulent Mixing

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.
  • Tribology (the study of the boundary interaction between sliding surfaces, lubrication, wear and friction).