A discrete vortex model for the calculation of aerodynamic loads on a blade of a N-bladed helicopter rotor in rectilinear flight

Simple item page
dc.contributor.advisorThiart, G. D.en_ZA
dc.contributor.authorArnold, Jacoben_ZA
dc.contributor.otherStellenbosch University. Faculty of Engineering. Department of Mechanical and Mechatronic Engineering.
dc.date.accessioned2012-08-27T12:27:07Z
dc.date.available2012-08-27T12:27:07Z
dc.date.issued1992
dc.descriptionThesis (M. Ing.) -- University of Stellenbosch, 1992.
dc.description.abstractENGLISH ABSTRACT: A model for the calculation of aerodynamic loads on a blade of a n-bladed helicopter rotor in rectilinear flight was developed and computerized. The model is based on a lifting line blade representation and a vortex lattice wake representation. Both a rigid and a semi-rigid wake geometry are available as options, while lifting line options include a classical and an extended lifting line representation. Viscous, unsteady and compressibility effects are also included as modelling options. Blade dynamics is restricted to rigid body flapping motion. A literature survey is presented, fundamental theoretical concepts are discussed, a mathematical model is derived and a discretized model is presented, including empirical modelling of blade profile aerodynamic characteristics. Calculated results are presented and compared with published experimental and calculated data, using different types of configurations and modelling options.en_ZA
dc.description.abstractAFRIKAANSE OPSOMMING: 'n Model vir die berekening van die lugdinamiese belading op die lem van 'n n-lem helikopterrotor is ontwikkel en gerekenariseer. Die model is gebaseer op 'n heflyn lemvoorstelling en 'n werwelrooster naloopvoorstelling. Beide 'n starre en 'n semi-starre naloopgeometriee is beskikbaar as opsies, terwyl heflyn modelleringsopsies 'n klassieke en 'n verlengde heflynvoorstelling behels. Die effekte van viskositeit, onbestendige vloei en samedrukbaarheid is ook as modelleringsopsies ingesluit. Lemdinamika is beperk tot starliggaam flapbeweging. 'n Literatuuroorsig word gelewer, fundamentele teoretiese konsepte word bespreek, en 'n wiskundige model word afgelei, gediskretiseer en geprogrammeer, insluitend empiriese modellering van die lugdinamiese karakteristieke van die lemprofiel. Berekende resultate word aangebied en vergelyk met gepubliseerde eksperimentele en berekende data, deur verskillende rotorkonfigurasies en modelleringsopsies te beskou.af_ZA
dc.format.extent269 pages : illustrations.
dc.identifier.urihttp://hdl.handle.net/10019.1/69490
dc.language.isoen_ZA
dc.publisherStellenbosch : Stellenbosch University
dc.rights.holderStellenbosch University
dc.subjectRotors (Helicopters) -- Mathematical modelsen_ZA
dc.subjectBlades -- Mathematical modelsen_ZA
dc.subjectAerodynamicsen_ZA
dc.subjectDissertations -- Mechanical engineeringen_ZA
dc.subjectUCTDen_ZA
dc.titleA discrete vortex model for the calculation of aerodynamic loads on a blade of a N-bladed helicopter rotor in rectilinear flighten_ZA
dc.typeThesis
Files
Original bundle
Now showing 1 - 1 of 1
Thumbnail Image
Name:
arnold_discrete_1992.pdf
Size:
42.74 MB
Format:
Adobe Portable Document Format
Description:
Download Thesis
Download
Collections
Masters Degrees (Mechanical and Mechatronic Engineering)