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The Global ETD Search service is a free service for researchers
to find electronic theses and dissertations. This service is
provided by the
Networked Digital Library of Theses and Dissertations.
Our metadata is collected from universities around the world. If you manage a university/consortium/country archive and want to be added, details can be found on the NDLTD website.
Search results
Showing 1 to 10 of 17 (0.008 seconds)| 1 |
A short-stroke permanent magnet actuator for a smart helicopter rotorLangley, Felix Lawrence January 2006 (has links)
No description available.
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Vibration reduction in helicopters using lag dampersEyres, Richard David January 2005 (has links)
No description available.
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Safety factors and risk in fatigue substantiation of helicopter componenetsToulas, N. January 2005 (has links)
No description available.
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Impact response of composite helicopter rotor bladesTurnock, Wingyan Wong January 2004 (has links)
No description available.
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Application of airjet vortex generators to control helicopter retreating blade stallSingh, Chrisminder January 2006 (has links)
No description available.
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Helicopter response to vortex encounters in the near airfield environmentWhitehouse, Glen Robert January 2004 (has links)
No description available.
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A CFD investigation of synthetic jetsMacpherson, Iain January 2003 (has links)
No description available.
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Analysis and indicial modelling of helicopter tail rotor orthogonal blade vortex interactionSuttie, David R. January 2006 (has links)
No description available.
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Helicopter flight control system design using sliding mode theory : application to handling qualities and shipboard landingMcGeoch, David James January 2005 (has links)
No description available.
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The development of a boundary layer transition model for helicopter rotor CFDHill, Jason Lee January 2005 (has links)
A novel transition model has been developed for use in CFD simulations of helicopter rotor aerodynamics. The model includes significantly improved physical modelling of the transition processes occurring in the steady and unsteady flows found on helicopter rotors. The model has been coupled with the k-co and k-co SST two equation turbulence models using a novel adaptation of the technique developed by Wilcox for the low Reynolds number k-oa model. The method has been employed to calculate transitional flows occurring in three key ow regimes found in helicopter aerodynamics; that around steady and unsteady aerofoils and that around a hovering helicopter rotor. The performance of the k-co and the k-w SST turbulence models have been investigated for transitional flow simulations and the k-w SST shown to provide substantial improvements for transitional flows containing separations. Dramatic improvements in the computed pressure and skin friction distributions for several aerofoil flows have been observed over those computed using a conventional fully turbulent simulation. Corresponding improvements are observed in the computed lift and drag polars and transition on set is well predicted for both low and high Reynolds number flows. A novel structured/unstructured a priori adapted grid generation strategy has been developed for hovering rotor flows that provides improved rotor solutions for transitional flow analysis. The method offers vast improvements in the preservation of vorticity in the solution at greatly reduced computational expense. Tip vortices have been maintained to a Wake age of 1170 degrees with just 2 million cells per blade. The transition model has then been applied to the high quality rotor solutions and good agreement obtained between computed and experimental results, highlighting that three-dimensional effects have a relatively small effect on hovering rotor transition in-board of the blade tip. I addition, the first known verification of a Navier-Stokes rotor code against the Fogarty semi-analytical rotating at plate case was presented and excellent agreement obtained.
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