NDLI: Static aeroelasticity of a composite oblique wing in transonic flows

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Static aeroelasticity of a composite oblique wing in transonic flows

Content Provider	NASA Technical Reports Server (NTRS)
Author	Bohlmann, Jonathan D.
Copyright Year	1989
Description	One aircraft configuration that shows great promise in achieving high performance is that of an asymmetrically swept wing. When compared to conventional swept wings, these advantages include higher lift to drag ratios and reduced takeoff and landing speeds, which translate into greater performance in terms of fuel comsumption, loiter time, and range. However, the oblique wing has a number of disadvantages because of its asymmetric configuration. The question is how to best achieve maximum stability and roll equilibrium without compromising performance. Using aeroelastic tailoring to enhance aeroelastic stability and control has been demonstrated in several analyses, especially for the forward swept wing. The advantages and disadvantages for the oblique wing configuration are discussed.
File Size	405555
Page Count	11
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19890009883
Archival Resource Key	ark:/13960/t9w13zr65
Language	English
Publisher Date	1989-02-01
Access Restriction	Open
Subject Keyword	Aerodynamics Oblique Wings Transonic Flow Stress Intensity Factors Airfoil Profiles Swept Wings Computational Fluid Dynamics Unsteady Aerodynamics Flow Distribution Composite Structures Aeroelasticity Aircraft Configurations Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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