Static internal performance of single-expansion-ramp nozzles with thrust-vectoring capability up to 60 deg

Author: Berrier, B. L.
Published: Oct 1, 1984.
Physical Description: 1 electronic document
Additional Creators: Leavitt, L. D.

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Summary

An investigation has been conducted at static conditions (wind off) in the static-test facility of the Langley 16-Foot Transonic Tunnel. The effects of geometric thrust-vector angle, sidewall containment, ramp curvature, lower-flap lip angle, and ramp length on the internal performance of nonaxisymmetric single-expansion-ramp nozzles were investigated. Geometric thrust-vector angle was varied from -20 deg. to 60 deg., and nozzle pressure ratio was varied from 1.0 (jet off) to approximately 10.0.

Other Subject(s)

AERODYNAMICS

Collection

NASA Technical Reports Server (NTRS) Collection.

Note

Document ID: 19870001406.
Accession ID: 87N10839.
L-15766.
NASA-TP-2364.
NAS 1.60:2364.

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