An Evaluation of Wind Tunnel Test Techniques for Aircraft Nozzle Afterbody Testing at Transonic Mach Numbers

Abstract

The results of many experiments to develop and verify wind tunnel test techniques for determining engine exhaust effects on aircraft performance at transonic Mach numbers are summarized. The influence of model support interference, exhaust jet simulation techniques, wind tunnel calibration-flow quality and operating conditions, model geometric effects, and measurement techniques n afterbody aerodynamic forces are discussed. Recommendations are given for reducing or eliminating adverse interference effects on wind tunnel test data.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1980
Accession Number
ADA091775

Entities

People

  • T. L. Kennedy

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Forces
  • Afterbodies
  • Aircrafts
  • Calibration
  • Cooperation
  • Mach Number
  • Measurement
  • Simulations
  • Test And Evaluation
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerospace Test and Evaluation
  • Combustion and Flow Dynamics.
  • Fluid Dynamics.