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Development of an efficient procedure for calculating the aerodynamic effects of planform variation

Author
Geller, E. W.
Published
Dec 1, 1981.
Physical Description
1 electronic document
Additional Creators
Mercer, J. E.
Online Version

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Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access
Summary
Numerical 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.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19820006656.
Accession ID: 82N14529.
FLOW-RR-186.
NASA-CR-3489.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15717359