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Static aeroelastic analysis of a three-dimensional oblique wingA capability to perform static aeroelastic analyses of an oblique wing at arbitrary skew positions was developed based on the framework of the MSC/NASTRAN static aeroelastic analysis. By means of DMAP alterations, a portion of the subsonic static aeroelastic analysis scheme was modified to insert an aerodynamic influence coefficient matrix created externally by the NASA-Ames aerodynamic panel codes. The modified scheme can cover the subsonic as well as the supersonic range for both symmetric and asymmetric configurations. Static aeroelastic responses of the oblique wing are studied at two skew angles and, in particular, the capability to calculate 3D camber effects on the aerodynamic properties of the wing is investigated. Various aerodynamic coefficients of the rigid oblique wing are computed for two Mach numbers, 0.7 and 1.4, and the angle of attack is varied from -5 through 15 deg. Also, the wing flexibility effects on the aerodynamic coefficients and the displacement are examined at a Mach number of 0.7 for a 45-deg swept wing.
Document ID
19910058088
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Lee, I.
(Korea Advanced Institute of Science and Technology Seoul, Republic of Korea, United States)
Miura, H.
(Korea Advanced Inst. of Science and Technology Seoul (Republic of Korea)., United States)
Chargin, M. K.
(NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1990
Publication Information
Publication: Computing Systems in Engineering
Volume: 1
Issue: 2-4,
ISSN: 0956-0521
Subject Category
Aerodynamics
Accession Number
91A42711
Distribution Limits
Public
Copyright
Other

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