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Potential flow calculations and preliminary wing design in support of an NLF variable sweep transition flight experimentNASA Langley and NASA Ames-Dryden have defined a variable-sweep transition-flight experiment utilizing the F-14 aircraft to enhance understanding of the interaction of crossflow and Tollmien-Schlichting instabilities on a laminar-boundary-layer transition. The F-14 wing outer panel will be modified to generate favorable pressure gradients on the upper wing surface over a wide range of flight conditions. Extensive computations have been performed using two-dimensional and three-dimensional transonic analysis codes. Flight-test and computational data are compared and shown to validate the applicability of the three-dimensional codes (WBPPW and TAWFIVE). In addition, results from two preliminary glove designs derived from two different approaches to the design problem are presented. Advantages and disadvantages of each approach are identified, and it is concluded that coupling an analysis code with an automated design procedure yields a powerful code with distinct advantages over a 'cut-and-dry' approach.
Document ID
19850037590
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Waggoner, E. G.
(NASA Langley Research Center Hampton, VA, United States)
Phillips, P. S.
(NASA Langley Research Center Hampton, VA, United States)
Viken, J. K.
(Mandex, Inc. Falls Church, VA, United States)
Davis, W. H.
(Grumman Aerospace Corp. Bethpage, NY, United States)
Date Acquired
August 12, 2013
Publication Date
January 1, 1985
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 85-0426
Accession Number
85A19741
Distribution Limits
Public
Copyright
Other

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