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A wing concept for supersonic maneuveringA theoretical and experimental program in which a wing concept for supersonic maneuvering was developed and then demonstrated experimentally in a series of wind tunnel tests is described. For the typical fighter wing, the problem of obtaining efficient lift at supersonic maneuvering C sub 's occurs due to development of a strong crossflow shock, and boundary layer separation. A natural means of achieving efficient supersonic maneuvering is based on controlling the non-linear inviscid crossflow on the wing in a manner analogous to the supercritical aerodynamic methods developed for transonic speeds. The application of supercritical aerodynamics to supersonic speeds is carried out using Supercritical Conical Camber (SC3). This report provides an aerodynamic analysis of the effort, with emphasis on wing design using non-linear aerodynamics. The substantial experimental data base is described in three separate wind tunnel reports, while two of the computer programs used in the work are also described in a separate report. Based on the development program it appears that a controlled supercritical crossflow can be obtained reliably on fighter-type wing planforms, with an associated drag due to lift reduction of about 20% projected using this concept.
Document ID
19840007047
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Mason, W. H. (Grumman Aerospace Corp. Bethpage, NY, United States)
Date Acquired
September 4, 2013
Publication Date
December 1, 1983
Publication Information
Publisher: NASA
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-3763
NAS 1.26:3763
Accession Number
84N15115
Funding Number(s)
CONTRACT_GRANT: NAS1-15357
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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