Actions for Static internal performance of ventral and rear nozzle concepts for short-takeoff and vertical-landing aircraft

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Static internal performance of ventral and rear nozzle concepts for short-takeoff and vertical-landing aircraft

Author
Re, Richard J.
Published
Sep 1, 1991.
Physical Description
1 electronic document
Additional Creators
Carson, George T., Jr.
Online Version

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Restrictions on Access
Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access
Summary
The internal performance of two exhaust system concepts applicable to single-engine short-take-off and vertical-landing tactical fighter configurations was investigated. These concepts involved blocking (or partially blocking) tailpipe flow to the rear (cruise) nozzle and diverting it through an opening to a ventral nozzle exit for vertical thrust. A set of variable angle vanes at the ventral nozzle exit were used to vary ventral nozzle thrust angle between 45 and 110 deg relative to the positive axial force direction. In the vertical flight mode the rear nozzle (or tailpipe flow to it) was completely blocked. In the transition flight mode flow in the tailpipe was split between the rear and ventral nozzles and the flow was vectored at both exits for aircraft control purposes through this flight regime. In the cruise flight mode the ventral nozzle was sealed and all flow exited through the rear nozzle.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19920001757.
Accession ID: 92N10975.
NAS 1.60:3103.
NASA-TP-3103.
L-16902.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15678789