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dc.contributor.authorGawain, Theodore Henry
dc.date1973-12
dc.date.accessioned2013-03-07T21:51:42Z
dc.date.available2013-03-07T21:51:42Z
dc.date.issued1973-12
dc.identifier.urihttp://hdl.handle.net/10945/29697
dc.description.abstractIn the report, the standard wing equation, as normally derived from lifting line theory, is further refined and a solution procedure more basic than the usual collocation technique is developed. The calculation method adopted avoids the necessity of performing an explicit matrix inversion; all equations can be solved sequentially, one at a time. On the other hand this technique involves the evaluation of numerous integrals over the span. The calculations are cumulative, and can be carried as far as necessary to achieve any required degree of accuracy. The analysis is interesting not only for purposes of practical calculation but also for the light it sheds on the essential mathematical structure of the basic aerodynamic phenomena involved. This same general method of calculation can also be readily adapted to the solution of other common types of engineering problems. (Author)en_US
dc.description.urihttp://archive.org/details/alternativeformu00gawa
dc.language.isoen_US
dc.publisherMonterey, California. Naval Postgraduate Schoolen_US
dc.rightsThis publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.en_US
dc.subject.lcshFLUID DYNAMICS.en_US
dc.titleAn alternative formulation of the lifting line wing equation and its solutionen_US
dc.typeTechnical Reporten_US
dc.contributor.corporateNaval Postgraduate School (U.S.)
dc.subject.authorNAen_US
dc.description.funderNAen_US
dc.description.recognitionNAen_US
dc.identifier.oclcNA
dc.identifier.npsreportNPS-57GN73121A


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