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Canard configured aircraft with 2-D nozzleA closely-coupled canard fighter with vectorable two-dimensional nozzle was designed for enhanced transonic maneuvering. The HiMAT maneuver goal of a sustained 8g turn at a free-stream Mach number of 0.9 and 30,000 feet was the primary design consideration. The aerodynamic design process was initiated with a linear theory optimization minimizing the zero percent suction drag including jet effects and refined with three-dimensional nonlinear potential flow techniques. Allowances were made for mutual interference and viscous effects. The design process to arrive at the resultant configuration is described, and the design of a powered 2-D nozzle model to be tested in the LRC 16-foot Propulsion Wind Tunnel is shown.
Document ID
19780063995
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Child, R. D.
(Rockwell International Corp. Los Angeles, Calif., United States)
Henderson, W. P.
(NASA Langley Research Center Propulsion Aerodynamics Branch, Hampton, Va., United States)
Date Acquired
August 9, 2013
Publication Date
August 1, 1978
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 78-1450
Meeting Information
Meeting: Aircraft Systems and Technology Conference
Location: Los Angeles, CA
Start Date: August 21, 1978
End Date: August 23, 1978
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
78A47904
Distribution Limits
Public
Copyright
Other

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