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Propulsion integration for military aircraftThe transonic aerodynamic characteristics for high-performance aircraft are significantly affected by shock-induced flow interactions as well as other local flow interference effects which usually occur at transonic speeds. These adverse interactions can not only cause high drag, but can cause unusual aerodynamic loadings and/or severe stability and control problems. Many new programs are underway to develop methods for reducing the adverse effects, as well as to develop an understanding of the basic flow conditions which are the primary contributors. It is anticipated that these new programs will result in technologies which can reduce the aircraft cruise drag through improved integration as well as increased aircraft maneuverability throughh the application of thrust vectoring. This paper will identify some of the primary propulsion integration problems for high performance aircraft at transonic speeds, and demonstrate several methods for reducing or eliminating the undesirable characteristics, while enhancing configuration effectiveness.
Document ID
19900058394
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Henderson, William P.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 14, 2013
Publication Date
September 1, 1989
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
SAE PAPER 892234
Accession Number
90A45449
Distribution Limits
Public
Copyright
Other

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