The Analysis of Secondary Flows for Tube-Launched Rocket Configurations.

Abstract

Theoretical flow-fields have been calculated for various nozzle/launch-tube configurations using this flow model. The solutions, thus calculated, are compared with experimental data in the present paper. The principal objectives of the present paper are (1) to present an engineering model for the impingement flow-field which is produced when an underexpanded supersonic nozzle is exhausted into a constant-area tube, (2) to compare the computed flow-field solutions with experimental results, and (3) to use the comparisons to establish the validity of the flow model. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Jan 15, 1981
Accession Number
ADA096795

Entities

People

  • H. H. Korst
  • John J. Bertin

Organizations

  • University of Texas at Austin

Tags

Communities of Interest

  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Base Pressure
  • Boundary Layer
  • Exhaust Plumes
  • Flow Fields
  • Fluid Dynamics
  • Geometry
  • Inviscid Flow
  • Launch Tubes
  • Mach Number
  • Pressure Distribution
  • Pressure Gradients
  • Pressure Measurement
  • Rocket Exhaust
  • Stagnation Pressure
  • Tube Launched
  • Turbulent Mixing
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Computational Modeling and Simulation

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow