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Computational wing design in support of an NLF variable sweep transition flight experimentA natural laminar flow outer panel wing glove has been designed for a variable sweep fighter aircraft using state-of-the-art computational techniques. Testing of the design will yield wing pressure and boundary-layer data under actual flight conditions and environment. These data will be used to enhance the understanding of the interaction between crossflow and Tollmien-Schlichting disturbances on boundary-layer transition. The outer wing panel was contoured such that a wide range of favorable pressure gradients could be obtained on the wing upper surface. Extensive computations were performed to support the design effort which relied on two- and three-dimensional transonic design and analysis techniques. A detailed description of the design procedure that evolved during this study is presented. Results on intermediate designs at various stages in the design process demonstrate how the various physical and aerodynamic constraints were integrated into the design. Final results of the glove design analyzed as part of the complete aircraft configuration with a full-potential wing/body analysis code indicate that the aerodynamic design objectives were met.
Document ID
19860026301
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Waggoner, E. G.
(NASA Langley Research Center Hampton, VA, United States)
Campbell, R. L.
(NASA Langley Research Center Hampton, VA, United States)
Phillips, P. S.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 12, 2013
Publication Date
October 1, 1985
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 85-4074
Accession Number
86A11039
Distribution Limits
Public
Copyright
Other

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