Evaluation of Reynolds Number and Tunnel Wall Porosity Effects on Nozzle Afterbody Drag at Transonic Mach Numbers

Abstract

An experimental investigation was conducted to study the effects of Reynolds number variation on isolated nozzle afterbody performance. A strut- mounted cone-cylinder model with three separate afterbody configurations for Aerospace Research and Development (AGARD) was used for this investigation. This program was conducted in two phases distinguished by the model size and the wind tunnels used to obtain the experimental results. The effect of tunnel wall porosity on nozzle afterbody (NAB) performance was investigated.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1976
Accession Number
ADA027388

Entities

People

  • C. E. Robinson

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerospace Industry
  • Afterbodies
  • Air Force
  • Bodies
  • Boundary Layer
  • Compressible Flow
  • Engineering
  • Flow
  • Fluid Dynamics
  • Geometry
  • Instrumentation
  • Pressure Distribution
  • Pressure Measurement
  • Reynolds Number
  • Static Pressure
  • Tennessee
  • Wind Tunnels

Readers

  • Aerodynamics/Aeronautics.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster