Shock Migration on an Oscillating Straked Delta Wing Using an Unsteady Euler Solver

Abstract

This research contributes to the understanding of Shock Induced Trailing Edge Separation (SITES) as a driver of Limit Cycle Oscillation (LCO) by performing a computational investigation of nonlinear aerodynamic phenomena on a straked delta wing in transonic flow, oscillating in pitch. ZEUS, an Euler-based aeroelastic solver with a boundary layer coupling scheme meant to capture viscous flow effects within the boundary layer, was used to analyze aerodynamic flow around the wing for various mean incidence angles, oscillation amplitudes, and Mach numbers within the transonic region. The dynamic characteristics of the airflow around the wing were investigated in order to characterize shock movement.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 2021
Accession Number
AD1137720

Entities

People

  • Alexander J Brown

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Aircrafts
  • Boundary Layer
  • Computational Fluid Dynamics
  • Flow Visualization
  • Fluid Dynamics
  • Fluid Flow
  • Fluid Mechanics
  • Hydrodynamics
  • Numerical Analysis
  • Pressure Distribution
  • Pressure Gradients
  • Reynolds Number
  • Three Dimensional
  • Transient Response Analysis
  • Viscous Flow
  • Wind Tunnel Tests

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Fluid Mechanics and Fluid Dynamics.