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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.
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Showing 31 to 40 of 60 (0.058 seconds)Spelling suggestions: "subject:"fgotors (helicopters)aerodynamics"" "subject:"fgotors (helicopters)neurodynamics""
| 31 |
Identification of an improved body aerodynamics model for the BO 105Bitzer, Michael 12 1900 (has links)
No description available.
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| 32 |
Towards a unified analysis methodology for composite rotor bladesAtilgan, Ali Rana 08 1900 (has links)
No description available.
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| 33 |
Application of a state-space wake model to a servo flap controlled rotor in hoverStettner, Martin 12 1900 (has links)
No description available.
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| 34 |
Computation of helicopter rotor wake geometry and its influence on rotor harmonic airloadsScully, M. (Michael) January 1975 (has links)
Thesis. 1975. Ph.D.--Massachusetts Institute of Technology. Dept. of Aeronautics and Astronautics. / Vita. / Includes bibliographical references. / by Michael P. Scully. / Ph.D.
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| 35 |
Aerodynamic shape optimization via control theory of helicopter rotor blades using a non-linear frequency domain approachTatossian, Charles A. January 2008 (has links)
This study presents a discrete adjoint-based aerodynamic optimization algorithm for helicopter rotor blades in hover and forward flight using a Non-Linear Frequency Domain approach. The goal is to introduce a Mach number variation into the Non-Linear Frequency Domain (NLFD) method and implement a novel approach to present a time-varying cost function through a multi-objective adjoint boundary condition. The research presents the complete formulation of the time dependent optimal design problem. The approach is firstly demonstrated for the redesign of a NACA 0007 and a NACA 23012 helicopter rotor blade section in forward flight. A three-dimensional inviscid Aerodynamic Shape Optimization (ASO) algorithm is then employed to validate and redesign the Caradonna and Tung experimental blade. The results in determining the optimum aerodynamic configurations require an objective function which minimizes the inviscid torque coefficient and maintains the desired thrust level at transonic conditions.
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| 36 |
Aerodynamic interactions between bodies in relative motionSchreiber, Olivier 08 1900 (has links)
No description available.
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| 37 |
Finite difference techniques and rotor blade aeroelastic partial differential equations with quasisteady aerodynamicsYillikci, Yildirim Kemal 12 1900 (has links)
No description available.
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| 38 |
Development and validation of a generalized ground effect model for lifting rotorsXin, Hong 08 1900 (has links)
No description available.
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| 39 |
Unsteady vortex lattice aerodynamics for rotor aeroelasticity in hover and in forward flightYoo, Kyung M. 12 1900 (has links)
No description available.
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| 40 |
A method for the efficient calculation of elastic rotor blade dynamic response in forward flightTaylor, Dana J. 05 1900 (has links)
No description available.
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