Thrust-Induced Effects on a Pitching-Up Delta Wing Flow Field.

Abstract

Experimental study of thrust-induced effects on a pitching-up 60 deg. delta wing was conducted. A downward vectored trailing edge jet has a significant effect in delaying the vortex breakdown. Strong asymmetric vortex bursting can be induced using asymmetric jet control. Detailed PIV measurements are taken to characterize the vortex flow field with and without jet control. A parallel experiment of the vortex flow over a 75 deg. delta wing is made to further the understanding of th vortex breakdown phenomenon. Related investigations of dynamic stall phenomena over a pitching airfoil are also summarized. Concurrently, considerable efforts have been made in the development of an innovative computational scheme. A grid-free vortex distribution technique is introduced to simulate the diffusion process of a vortex-dominated flow. This allows the readily extension of the 2-D vortex method to be used in a 3-D flow field such as a pitching-up delta wing configuration. Several computational examples will be discussed.

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Document Details

Document Type
Technical Report
Publication Date
May 23, 1996
Accession Number
ADA310244

Entities

People

  • A. Krothapaili
  • Chung-You Shih
  • L. Lourenco
  • L. Van Dommelen

Organizations

  • Florida A&M University

Tags

Communities of Interest

  • Materials and Manufacturing Processes
  • Space

DTIC Thesaurus Topics

  • Boundary Layer
  • Brushless Dc Motors
  • Computational Fluid Dynamics
  • Computational Science
  • Delta Wings
  • Flow
  • Flow Fields
  • Flow Visualization
  • Fluid Dynamics
  • Lasers
  • Measurement
  • Reynolds Number
  • Three Dimensional
  • Trailing Edges
  • Turbulent Mixing
  • Two Dimensional

Fields of Study

  • Physics

Readers

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