Email RIS file
Bookmark
Report an Issue

Effect of nozzle and vertical-tail variables on the performance of a 3-surface F-15 model at transonic Mach numbers

Author
Bare, E. A.
Published
Aug 1, 1982.
Physical Description
1 electronic document
Additional Creators
Pendergraft, O. C., Jr.
Online Version

Availability

I Want It
I Want It

Finding items...

Restrictions on Access
Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access
Summary
An investigation was conducted in the Langley 16 foot transonic tunnel to determine the longitudinal aerodynamic characteristics of twin two dimensional nozzles and twin baseline axisymmetric nozzles installed on a fully metric 0.047 scale model of the F-15 three surface configuration (canards, wing, horizontal tails). The effects on performance of two dimensional nozzle in flight thrust reversing, locations and orientation of the vertical tails, and deflections of the horizontal tails were also determined. Test data were obtained at static conditions and at Mach numbers from 0.60 to 1.20 over an angle of attack range from -2 deg to 15 deg. Nozzle pressure ratio was varied from jet off to about 6.5.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19820024444.
Accession ID: 82N32320.
L-15304.
NASA-TP-2043.
NAS 1.60:2043.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15714965