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Evaluation of Four Advanced Nozzle Concepts for Short Takeoff and Landing PerformanceFour advanced nozzle concepts were tested on a canard-wing fighter in the Langley 14- by 22-Foot Subsonic Tunnel. The four vectoring-nozzle concepts were as follows: (1) an axisymmetric nozzle (AXI); (2) an asymmetric, load balanced exhaust nozzle (ALBEN); (3) a low aspect ratio, single expansion ramp nozzle (LASERN); and (4) a high aspect ratio, single expansion ramp nozzle (HASERN). The investigation was conducted to determine the most suitable nozzle concept for short takeoff and landing (STOL) performance. The criterion for the best STOL performance was a takeoff ground roll of less than 1000 ft. At approach, the criteria were high lift and sufficient drag to maintain a glide slope of -3 to -6 deg with enough pitching-moment control from the canards. The test was performed at a dynamic pressure of 45 lb/sq ft and an angle-of-attack range of 0 to 20 deg. The nozzle pressure ratio was varied from 1.0 to 4.3 at both dry power and after burning nozzle configurations with nozzle vectoring to 60 deg. In addition, the model was tested in and out of ground effects. The ALBEN concept was the best of the four nozzle concepts tested for STOL performance.
Document ID
19930019976
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Quinto, P. Frank (NASA Langley Research Center Hampton, VA, United States)
Kemmerly, Guy T. (NASA Langley Research Center Hampton, VA, United States)
Paulson, John W., Jr. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
June 1, 1993
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.60:3314
NASA-TP-3314
L-16998
Accession Number
93N29165
Funding Number(s)
PROJECT: RTOP 505-59-30-02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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