Analysis and Comparison of Several Methods for Computing Aerodynamic Compressibility and Interference Effects up to Critical Mach Numbers.

Abstract

Analytical approaches are considered which might be used to improve and extend current aerodynamic analysis to include the compressibility effects up to and including critical mach numbers. The Rayleigh-Janzen solution is considered for both small disturbance and exact potential flows. A simple numerical method is presented and compared with both experimental results and the results of other analytical methods for potential flow. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1977
Accession Number
ADA050267

Entities

People

  • Brent D. Martin
  • Fred W. Martin
  • James Purvis
  • John E. Burkhalter

Organizations

  • Auburn University

Tags

Communities of Interest

  • Air Platforms
  • Counter IED
  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aircrafts
  • Boundary Layer
  • Compressible Flow
  • Computational Fluid Dynamics
  • Computational Science
  • Difference Equations
  • Differential Equations
  • Finite Element Analysis
  • Flow Fields
  • Fluid Dynamics
  • Fluid Flow
  • Fluid Mechanics
  • Geometry
  • Hydrodynamics
  • Partial Differential Equations
  • Pressure Distribution
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.