Accession Number:

ADB037421

Title:

Wind Tunnel Results from a Nozzle Afterbody Test of a 0.2-Scale Fighter Aircraft in the Mach Number Regime of 0.6 to 1.5. Volume II. Model Configuration and Environment Effects.

Descriptive Note:

Final rept. Jul 1977-Sep 1978

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN

Personal Author(s):

Report Date:

1979-05-01

Pagination or Media Count:

349.0

Abstract:

An investigation was conducted in the Propulsion Wind Tunnel 16T to document the effect of throttle-dependent parameters nozzle closure and nozzle pressure ratio on the aft end surface pressures of a 0.2-scale model of a twin- engine fighter prototype YF-17. The data are part of a data base to be used in a future analysis effort to define the validity of current wind tunnel test techniques to provide data for full-scale flight performance predictions.

Subject Categories:

  • Aerodynamics
  • Attack and Fighter Aircraft
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE