Model Diffuser Investigation for Propulsion Wind Tunnel 16T

Abstract

A 1/16-scale model of the diffuser of the Propulsion Wind Tunnel (16T) was installed and tested in the Aerodynamic Wind Tunnel (1T). Objectives of the test were to evaluate the effectiveness of a number of geometric modifications of the diffuser to improve diffuser performance. Thirteen configurations involving combinations of six geometric modifications were evaluated in the tunnel Mach number range from 0.60 to 1.50.

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Document Details

Document Type
Technical Report
Publication Date
Nov 09, 1978
Accession Number
ADA065822

Entities

People

  • L. J. David
  • M. G. Hale

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Autonomy

DTIC Thesaurus Topics

  • Air Force
  • Data Acquisition
  • Data Reduction
  • Engineering
  • Free Stream
  • Instrumentation
  • Leading Edges
  • Mach Number
  • Measurement
  • Measuring Instruments
  • Pressure Distribution
  • Pressure Measurement
  • Scale Models
  • Static Pressure
  • Test Facilities
  • Uncertainty
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Aerodynamics/Aeronautics.
  • Aerospace Test and Evaluation