3-D Composite Velocity Solutions for Subsonic/Transonic Flow Over Forebodies and Afterbodies

Abstract

A composite velocity procedure for the three-dimensional reduced Navier-Stokes equations is developed. In the spirit of matched asymptotic expansions, the velocity components are written as a combined multiplicative and additive composite of viscous like velocities (U, W) and pseudo-potential or inviscid velocities (phi sub x, phi sub y, phi sub z). The solution procedure is then consistent with both asymptotic inviscid flow and boundary layer theory. For transonic flow cases, the Enquist-Osher flux biasing scheme developed for the full potential equation is used. A quasi-conservation form of the governing equation is used in the shock region to capture the correct rotational behavior. This is combined with the standard nonconservation nonentropy generating form used in nonshock regions. The consistent strongly implicit procedure is coupled with plane relaxation to solve the discretized equations. The composites velocity procedure is coupled with plane relaxation to solve the discretized equations. The composits velocity procedure applied for the solution of three-dimensional afterbody problems.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1989
Accession Number
ADA220370

Entities

People

  • Raymond E. Gordnier

Organizations

  • Universal Energy Systems

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Asymptotic Series
  • Boundary Layer
  • Computational Fluid Dynamics
  • Difference Equations
  • Differential Equations
  • Equations
  • Flow
  • Fluid Dynamics
  • Fluid Flow
  • Geometry
  • Inviscid Flow
  • Layers
  • Navier Stokes Equations
  • Standards
  • Three Dimensional
  • Transonic Flow
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Adaptive Control and Estimation with Uncertainty in Dynamic Systems.
  • Aerodynamics/Aeronautics.
  • Fluid Dynamics.