Thin Layer Navier-Stokes Solutions for Transonic Multibody Interference

Abstract

A thin layer, Navier Stokes flow solver was used to predict the aerodynamics about interfering bodies. Surface pressure distributions compared very well with available experimental data for freestream Mach numbers between 0.60 and 1.20 at an interbody separation distance of 0.8 diameters. Five separate interference regions were identified which contribute to the total interference force, which was an attractive force for all cases investigated. In general, the level of interference increases with increasing free stream Mach number, and decreases with increasing separation distance.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1991
Accession Number
ADA234252

Entities

People

  • Magdi H. Rizk
  • Prisca L. Lynch

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Abstracts
  • Aerodynamics
  • Boundaries
  • Computational Fluid Dynamics
  • Diameters
  • Experimental Data
  • Flow
  • Fluid Dynamics
  • Fluid Flow
  • Free Stream
  • Mach Number
  • Measurement
  • Mechanics
  • Pressure Distribution
  • Reflection
  • Transitions
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Computational Fluid Dynamics (CFD)
  • Fluid Dynamics.