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Combined, nonlinear aerodynamic and structural method for the aeroelastic design of a three-dimensional wing in supersonic flowAn iterative procedure for the static aeroelastic design of a flexible wing at supersonic speeds has been developed. The procedure combines a nonlinear, full-potential solver (NCOREL) with an equivalent plate structural analysis method. The NCOREL method yields significantly improved aerodynamic estimates compared to linear theory. The equivalent plate structural analysis method demonstrates an order of magnitude reduction in computer memory and execution time compared to finite-element methods. A highly swept wing is analyzed at high lift using this aeroelastic procedure. The results indicate that the wing deforms favorably due to aerodynamic loading and, consequently, that the inviscid drag levels do not vary at the required lift coefficient although the angle of attack varies significantly. A sensitivity analysis of the type required for optimization studies was also performed with the aeroelastic design procedure.
Document ID
19860053068
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Pittman, J. L.
(NASA Langley Research Center Hampton, VA, United States)
Giles, G. L.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 12, 2013
Publication Date
January 1, 1986
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 86-1769
Accession Number
86A37806
Distribution Limits
Public
Copyright
Other

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