A Numerical Method For Unsteady Transonic Flow About Wings With Control Surfaces,

Abstract

This article introduces a type of finite difference calculation method for unsteady transonic speed flows associated with wings having control surfaces. The equations which are chosen for use are modified three dimensional nonsteady transonic speed small perturbation geopotential equations. Use is made of time integration methods. Solution forms are approximate factor type resolutions of alternating direction implicit (ADI) type forms. Use is made of this type of method to calculate the unsteady aerodynamic forces associated with F-5 wings in oncoming flows with Mach numbers or 0.9 and 0.925 as well as the unsteady aerodynamic forces associated with control surface oscillations. Comparisons were carried out of calculation results with NLR test results from outside of China and calculation results from XTRAN3S methods. This clearly showed that calculations were successful.

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Document Details

Document Type
Technical Report
Publication Date
Dec 15, 1994
Accession Number
ADA289631

Entities

People

  • Jianbai Zhang
  • Tao Yu

Organizations

  • National Air and Space Intelligence Center

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Configurations
  • Aerodynamic Forces
  • Air Intelligence
  • Aircraft Wings
  • Aircrafts
  • Boundaries
  • Control Surfaces
  • Flow
  • Frequency
  • Mach Number
  • Pressure Distribution
  • Shock Waves
  • Steady State
  • Three Dimensional
  • Trailing Edges
  • Transonic Flow
  • Waves

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)
  • Fluid Mechanics and Fluid Dynamics.