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Static aeroelastic analysis of a three-dimensional generic wingA continuation of research on the static aeroelastic analysis of a generic wing configuration is presented. Results of the study of the asymmetric oblique wing model developed by Rockwell International, in conjunction with the NASA Oblique Wing Research Aircraft Program, are reported. The capability to perform static aeroelastic analyses of an oblique wing at arbitrary skew positions is demonstrated by applying the MSC/NASTRAN static analysis scheme modified by the aerodynamic influence coefficient matrix created by the NASA Ames aerodynamic panel codes. The oblique wing is studied at two skew angles, and in particular, the capability to calculate 3-D thickness effects on the aerodynamic properties of the wing is investigated. The ability to model asymmetric wings in both subsonic and supersonic Mach numbers is shown. The aerodynamic influence coefficient matrix computed by the external programs is inserted in MSC/NASTRAN static aeroelasticity analysis run stream to compute the aeroelastic deformation and internal forces. Various aerodynamic coefficients of the oblique wing were computed for two Mach numbers, 0.7 and 1.4, and the angle of attach -5 through 15 deg.
Document ID
19900010771
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Green, John A. (NASA Ames Research Center Moffett Field, CA, United States)
Lee, IN (NASA Ames Research Center Moffett Field, CA, United States)
Miura, Hirokazu (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 6, 2013
Publication Date
February 1, 1990
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
A-89239
NAS 1.15:102231
NASA-TM-102231
Accession Number
90N20087
Funding Number(s)
PROJECT: RTOP 533-06-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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