Show/Hide Menu
Hide/Show Apps
Logout
Türkçe
Türkçe
Search
Search
Login
Login
OpenMETU
OpenMETU
About
About
Open Science Policy
Open Science Policy
Communities & Collections
Communities & Collections
Help
Help
Frequently Asked Questions
Frequently Asked Questions
Guides
Guides
Thesis submission
Thesis submission
MS without thesis term project submission
MS without thesis term project submission
Publication submission with DOI
Publication submission with DOI
Publication submission
Publication submission
Supporting Information
Supporting Information
General Information
General Information
Copyright, Embargo and License
Copyright, Embargo and License
Contact us
Contact us
Aerodynamic investigation of a model scale helicopter rotor in ground effect
Download
index.pdf
Date
2017
Author
Şahbaz, Mehmet
Metadata
Show full item record
Item Usage Stats
206
views
93
downloads
Cite This
In this thesis, ground effect issue which is a vital topic for helicopter industry is investigated with model scale.For this purpose, a test setup with model helicopter rotor is established. With setup, ground effect is investigated with inclined ground and ground without inclination. Thrust and torque values are obtained for different rotation speeds with constant collective pitch. Comparison with literature is done and reliability of the test setup is proven. Inclined Ground Effect and Ground Effect with extreme proximity scenarios are tested. The proper trends of the performance parameters in these scenarios are obtained. For the sake of performance parameter alterations, CFD (Computational Fluid Dynamics) Method is applied to analyze the rotor downwash. To model the rotating helicopter blade, Single Moving Reference Frame Method (SMRF) is used. In this method, the blade and background mesh are kept still and rotational velocity is defined at each cell in the domain. With CFD results, flow physics is studied and performance changes in ground effect are explained.
Subject Keywords
Rotors (Helicopters).
,
Ground-cushion phenomenon.
,
Computational fluid dynamics.
,
Helicopters
URI
http://etd.lib.metu.edu.tr/upload/12621680/index.pdf
https://hdl.handle.net/11511/26881
Collections
Graduate School of Natural and Applied Sciences, Thesis
Suggestions
OpenMETU
Core
Flow characterization of full, partial, and inclined ground effect
Koçak, Göktuğ; Yavuz, Mehmet Metin; Nalbantoğlu, Volkan; Department of Mechanical Engineering (2016)
Flight condition of helicopters proximity to the ground, so-called “Ground Effect”, is among one of the most recent research areas since the aerodynamic performance of these vehicles significantly vary due to the flow dynamics associated with the interaction between the rotor and the surface. Thus, a comprehensive understanding of the rotor wake during in and out of ground effect is needed to improve the flight performance. Helicopters operate in ground effect in many different ways including full ground, p...
Aerodynamic modeling and parameter estimation of a quadrotor helicopter
Kaya, Derya; Kutay, Ali Türker (2014-01-01)
This study focuses on aerodynamic modeling of a quadrotor helicopter and the estimation of the model parameters in wind tunnel tests for hover, vertical climb, and forward flight conditions. The motion of a quadrotor is mainly affected by the aerodynamic forces and moments generated by rotors. Accurate calculation of rotor loads is essential for high fidelity simulation of a quadrotor. Momentum and blade element theories are used to obtain expressions for rotor forces and moments for a traveling vehicle. Th...
VERIFICATION OF A FINITE ELEMENT MODEL OF AN UNMANNED AERIAL VEHICLE WING TORQUE BOX VIA EXPERIMENTAL MODAL TESTING
Unlusoy, Levent; Şahin, Melin; Yaman, Yavuz (2012-07-04)
In this study, the detailed finite element model (FEM) of an unmanned aerial vehicle wing torque box was verified by the experimental modal testing. During the computational studies the free-free boundary conditions were used and the natural frequencies and mode-shapes of the structure were obtained by using the MSC Software. The results were then compared with the experimentally obtained resonance frequencies and mode-shapes. It was observed that the frequencies were in close agreement having an error with...
Experimental Investigation of Aerodynamics of Flapping-Wing Micro-Air-Vehicle by Force and Flow-Field Measurements
Deng, Shuanghou; Perçin, Mustafa; van Oudheusden, Bas (2016-02-01)
This study explores the aerodynamic characteristics of a flapping-wing micro aerial vehicle (MAV) in hovering configuration by means of force and flowfield measurements. The effects of flapping frequency and wing geometry on force generation were examined using a miniature six-component force sensor. Additional high-speed imaging allowed identification of the notable different deformation characteristics of the flexible wings under vacuum condition in comparison to their behavior in air, illustrating the re...
Numerical simulation of scour at the rear side of a coastal revetment
Şentürk, Barış Ufuk; Guler, Hasan Gokhan; Baykal, Cüneyt (2023-05-01)
This paper presents the results of a numerical modeling study on the scouring of unprotected rear side material of a rubble mound coastal revetment due to the overtopping of solitary-like waves utilizing a coupled hydro-morphodynamic computational fluid dynamics (CFD) model. Three cases having various wave heights are tested with six different turbulence models together with different wall functions. The hydrodynamic results (free-surface elevations, overtopping volumes, and jet thicknesses) and morphologic...
Citation Formats
IEEE
ACM
APA
CHICAGO
MLA
BibTeX
M. Şahbaz, “Aerodynamic investigation of a model scale helicopter rotor in ground effect,” M.S. - Master of Science, Middle East Technical University, 2017.
