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Development of an efficient procedure for calculating the aerodynamic effects of planform variationNumerical procedures to compute gradients in aerodynamic loading due to planform shape changes using panel method codes were studied. Two procedures were investigated: one computed the aerodynamic perturbation directly; the other computed the aerodynamic loading on the perturbed planform and on the base planform and then differenced these values to obtain the perturbation in loading. It is indicated that computing the perturbed values directly can not be done satisfactorily without proper aerodynamic representation of the pressure singularity at the leading edge of a thin wing. For the alternative procedure, a technique was developed which saves most of the time-consuming computations from a panel method calculation for the base planform. Using this procedure the perturbed loading can be calculated in about one-tenth the time of that for the base solution.
Document ID
19820006656
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Mercer, J. E.
(Flow Research, Inc. Kent, WA, United States)
Geller, E. W.
(Flow Research, Inc. Kent, WA, United States)
Date Acquired
September 4, 2013
Publication Date
December 1, 1981
Publication Information
Publisher: NASA
Subject Category
Structural Mechanics
Report/Patent Number
NASA-CR-3489
FLOW-RR-186
Accession Number
82N14529
Funding Number(s)
CONTRACT_GRANT: NAS1-15977
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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