STATIC AEROELASTIC ANALYSIS FOR GENERIC CONFIGURATION WING

A STATIC aeroelastic analysis capability that calculates flexible air loads for generic configuration wings was developed. It was made possible by integrating a finite element structural analysis code (MSC/NASTRAN) and a panel code of aerodynamic analysis based on linear potential flow theory. The framework already built in MSC/NASTRAN was used, and the aerodynamic influence coefficient matrix was computed externally and inserted in the NASTRAN by means of a DMAP program. It was shown that deformation and flexible air loads of an oblique wing configuration including asymmetric wings can be calculated reliably by this code both in subsonic and supersonic speeds.
Publisher
AMER INST AERONAUT ASTRONAUT
Issue Date
1991-12
Language
ENG
Citation

JOURNAL OF AIRCRAFT, v.28, no.12, pp.801 - 802

ISSN
0021-8669
URI
http://hdl.handle.net/10203/6274
Appears in Collection
NE-Journal Papers(저널논문)
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