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.
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.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1979
- Accession Number
- ADB037421
Entities
People
- Ernest J. Lucas
Organizations
- Arnold Engineering Development Complex