Accession Number:

ADA091775

Title:

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

Descriptive Note:

Final rept. 1 Oct 1977-1 Jan 1979

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN

Personal Author(s):

Report Date:

1980-11-01

Pagination or Media Count:

183.0

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.

Subject Categories:

  • Aerodynamics
  • Aircraft
  • Test Facilities, Equipment and Methods
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE