Accession Number:

ADB028240

Title:

Wind Tunnel Results from a Nozzle Afterbody Test of A 0.1-Scale Fighter Aircraft in the Mach Number Regime of 0.6 to 1.6

Descriptive Note:

Final rept. Jun 1975-Jan 1976

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN

Personal Author(s):

Report Date:

1978-06-01

Pagination or Media Count:

172.0

Abstract:

An investigation was conducted to obtain throttle-dependent aft end drag on a one-tenth scale model of a twin-engine fighter aircraft YF-17. These data will be used in assessing the validity of current wind tunnel data acquisition techniques. Pressure data were obtained for several configurations, using a wingtip support system, to define the effects of jet exhaust flow on afterbody pressure distributions. Data were also obtained with an dual sting support system and dummy wingtip booms to evaluate the interference introduced by the model wingtip support. This interference was on the order of twelve aircraft drag counts Delta C sub D 0.0012 at Mach number 1.2 and tended to decrease as the test Mach number was either increased or decreased. Changes in nozzle exit area for after-burning simulation produced significant local flow- field disturbances on the model aft end, but the increased pressure levels produced on the afterbody were compensated for by the decreased pressure levels on the nozzle so that the effect on the drag was less evident.

Subject Categories:

  • Aerodynamics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE