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 1. Test Technique Evaluation
Abstract
An investigation was conducted in the Propulsion Wind Tunnel (16T) to determine 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 wind tunnel/flight correlation to define the validity of current wind tunnel test techniques to provide data for full-scale flight performance predictions. Surface pressure data were obtained on several model configurations, using a wingtip support system, to define the effects of nozzle closure and jet exhaust flow on the test article nacelle and nozzle surfaces. Two additional test entries were conducted on sting support systems to evaluate support system interference produced by the wingtip support system and to evaluate the annular- jet test technique.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1979
- Accession Number
- ADB036406
Entities
People
- Ernest J. Lucas
Organizations
- Arnold Engineering Development Complex