An Improved Interaction Method for Calculating Exhaust Nozzle Boattail Flows

Abstract

A turbulent boundary-layer, inviscid flow interaction method for calculating axisymmetric nozzle boattail configurations is presented. The method is applicable to flows with subsonic or supersonic free streams with Mach number in the range 0.5 - 1.5, including flows with shock-wave induced separation and to bodies with either high pressure exhaust plumes or solid plume simulators. The theory and some sample calculations are presented along with detailed instructions for preparation of input data, description of output, and instructions for operation of the computer program on an IBM 370 computer.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1980
Accession Number
ADA091167

Entities

People

  • Gary D. Kuhn

Organizations

  • Nielsen Engineering & Research (United States)

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies
  • Space

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Boundary Layer Flow
  • Computational Fluid Dynamics
  • Computational Science
  • Computer Programs
  • Computers
  • Engineering
  • Exhaust Plumes
  • Flow Fields
  • Fluid Dynamics
  • Geometry
  • High Pressure
  • Inviscid Flow
  • Pressure Distribution
  • Turbulent Flow
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Computational Modeling and Simulation
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow