Boundary Layers Induced by Three-Dimensional Vortex Loops

Abstract

The flow field generated by a helicopter in flight is extremely complex and it has been recognized that interactions between different components can significantly affect helicopter performance. In particular, the effects of the interaction between the rotor wake and the helicopter fuselage are extremely difficult to predict and pose a challenging problem for researchers and designers in the rotorcraft area. In the present work, a model for the interaction of a rotor-tip-vortex with the airframe of a helicopter is developed. The present report describes the calculation of the motion of the tip-vortex toward the airframe, the calculation of the induced pressure on the airframe, and the calculation of the boundary-layer flow under the vortex during the time period prior to the time when a portion of the tip-vortex collides with the airframe.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1993
Accession Number
ADA275678

Entities

People

  • A. T. Conlisk
  • H. Affes
  • O. R. Burggraf
  • Zhenhua Xiao

Organizations

  • Ohio State University

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies
  • Sensors

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aircrafts
  • Airframes
  • Boundary Layer
  • Boundary Layer Flow
  • Computational Fluid Dynamics
  • Computational Science
  • Flow Fields
  • Flow Visualization
  • Fluid Dynamics
  • Fluid Flow
  • Helicopter Rotors
  • Hydrodynamics
  • Pressure Distribution
  • Turbulent Mixing
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Control Systems Engineering.
  • Structural Health Monitoring of Composite Structures.