A Comparison of Panel Methods for Subsonic Flow Computation,

Abstract

Panel, or surface singularity, methods have been developed to the stage where they provide nominally exact numerical solutions for incompressible flow potential around complicated, real aircraft configurations. A large variety of these methods are in use or under development. This report provides a data base against which the various programs may be checked and makes comparisons of several methods with the datum solutions for several simple wing configurations and nacelle configurations. Datum results are from the Roberts (BAe) Spline-Naumann Program, and a pilot version of the Boeing Advanced Panel-Type Influence Coefficient Method. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1979
Accession Number
ADA067171

Entities

People

  • B. L. Hewitt
  • H. S. Sytsma
  • P. E. Rubbert

Organizations

  • AGARD

Tags

Communities of Interest

  • Advanced Electronics
  • Counter WMD
  • Cyber
  • Space

DTIC Thesaurus Topics

  • Aircrafts
  • Boundaries
  • Computational Science
  • Equations
  • Flow
  • Fluid Dynamics
  • Geometry
  • Incompressible Flow
  • Integral Equations
  • National Security
  • Nato
  • Numerical Analysis
  • Operating Systems
  • Pressure Distribution
  • Subsonic Flow
  • Three Dimensional
  • United States

Fields of Study

  • Physics

Readers

  • Computational Modeling and Simulation
  • Fluid Dynamics.
  • Naval Engineering and Maritime Security