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The design of a wind tunnel VSTOL fighter model incorporating turbine powered engine simulatorsA wind-tunnel model of a supersonic VSTOL fighter aircraft configuration has been developed for use in the evaluation of airframe-propulsion system aerodynamic interactions. The model may be employed with conventional test techniques, where configuration aerodynamics are measured in a flow-through mode and incremental nozzle-airframe interactions are measured in a jet-effects mode, and with the Compact Multimission Aircraft Propulsion Simulator which is capable of the simultaneous simulation of inlet and exhaust nozzle flow fields so as to allow the evaluation of the extent of inlet and nozzle flow field coupling. The basic configuration of the twin-engine model has a geometrically close-coupled canard and wing, and a moderately short nacelle with nonaxisymmetric vectorable exhaust nozzles near the wing trailing edge, and may be converted to a canardless configuration with an extremely short nacelle. Testing is planned to begin in the summer of 1982.
Document ID
19820041619
Document Type
Conference Paper
Authors
Bailey, R. O. (NASA Ames Research Center Moffett Field, CA, United States)
Maraz, M. R. (NASA Ames Research Center Moffett Field, CA, United States)
Hiley, P. E. (Douglas Aircraft Co. St. Louis, MO, United States)
Date Acquired
August 10, 2013
Publication Date
December 1, 1981
Subject Category
RESEARCH AND SUPPORT FACILITIES (AIR)
Report/Patent Number
AIAA PAPER 81-2635
Meeting Information
V/STOL Conference(Palo Alto, CA)
Funding Number(s)
CONTRACT_GRANT: F33615-77-C-2097
Distribution Limits
Public
Copyright
Other