Research on Post-Stall Aerodynamics.

Abstract

Fundamental results for two and three dimensional unsteady flows are derived. A model for vortex shedding at salient edges is advanced. A two dimensional Euler solver that implements this vortex shedding mechanism is described. Results of applying this model to impulsively started flat plates with fixed and with oscillating chord at angle of attack ate presented. Implications for manipulation of the vortex wake in a post stall maneuver are discussed. A three dimensional unsteady Euler solver based on primitive variables is described. Results of three dimensional computations for delta wing at fixed and time varying angle of attack are presented. Keywords: Post Stall Maneuverability; Separated Flow; Unsteady Aerodynamics; Vortex Shedding.

Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1986
Accession Number
ADA177107

Tags

DTIC Thesaurus Topics

  • Aerodynamics
  • Delta Wings
  • Flow
  • Fluid Dynamics
  • Fluid Flow
  • Maneuverability
  • Maneuvers
  • Three Dimensional
  • Two Dimensional
  • Unsteady Aerodynamics
  • Unsteady Flow
  • Vortex Shedding
  • Vortices

Fields of Study

  • Physics

Readers

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