Show/Hide Menu
Hide/Show Apps
Logout
Türkçe
Türkçe
Search
Search
Login
Login
OpenMETU
OpenMETU
About
About
Open Science Policy
Open Science Policy
Open Access Guideline
Open Access Guideline
Postgraduate Thesis Guideline
Postgraduate Thesis Guideline
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
Navier-Stokes computations of helicopter rotor flow fields
Download
index.pdf
Date
2017
Author
Yüksel, Ali Oğuz
Metadata
Show full item record
Item Usage Stats
337
views
186
downloads
Cite This
Helicopters are widely used for military and civilian purposes because of their unique capability of maneuvering including vertical take-off and landing. A helicopter rotor provides this capability of motion with rotating wings. Aerodynamic forces on rotor blades generate the thrust and torque. Hence, it is significant to predict pressure distributions on rotor blades in hover, climbing, descending, and forward flight, for assessing the helicopter performance. Not only this but acoustic radiation from helicopter rotors also depends on the rotor load distributions. Motivated by these points, the objective of the thesis is to carry out flow solutions of helicopter rotors in hover and forward flight. The thesis involves numerical solutions of both Euler and Reynolds-Averaged Navier-Stokes equations. Commercial software, Ansys Fluent is used together with its User Defined Function capability to handle moving meshes. To assess the success of User Defined Function capability for providing cyclic motion, comparisons with analytical blade motion are carried out. Then, numerical flow solutions over rotor blades are compared with available experimental and numerical results from literature. Results indicate good agreement. Aerodynamic load distributions on rotating blades and flow field solutions around some of the computed rotors are also used as input into a noise prediction code developed under a separate work which has been supported by the Turkish Aerospace Industry, Inc. RotaryWing Technological Center. Sound pressure levels predicted employing the flow solutions obtained in this thesis are also presented.
Subject Keywords
Helicopters.
,
Aerodynamics.
,
Rotors (Helicopters).
,
Navier-Stokes equations.
,
Computational fluid dynamics.
URI
http://etd.lib.metu.edu.tr/upload/12621590/index.pdf
https://hdl.handle.net/11511/26775
Collections
Graduate School of Natural and Applied Sciences, Thesis
Suggestions
OpenMETU
Core
Parametric investigation of hull shaped fuselage for amphibious UAV
Sazak, Emre; Kurtuluş, Dilek Funda; Department of Aerospace Engineering (2017)
Performance of amphibious unmanned aerial vehicles (UAV’s) that take off from and land on water, like seaplanes, greatly depend on hydrodynamic effects as well as aerodynamic effects, therefore their geometries need to be optimized for both. This study mainly investigates the effect of geometric parameters of a generic, hull-shaped fuselage that are constrained by hydrodynamic drivers, such as the step height needed to reduce hydrodynamic drag, sternpost angle and deadrise angle needed for safe landing; on ...
Design and evaluation of a helicopter main rotor electrohydraulic control system
Düzağaç, Hasan Ali; Çalışkan, Hakan; Balkan, Raif Tuna; Department of Mechanical Engineering (2022-8-26)
Helicopters are widely used aircrafts for several purposes. Main Rotor of a Helicopter creates necessary flight forces for performing flight operation. Orientation of a Helicopter Rotor System is determined and controlled manually by pilot and automatically by automatic control system via hydraulically operated flight control actuators. In this research, a novel electrohydraulically operated helicopter main rotor control system is mathematically designed and developed to improve overall performance of contr...
An algorithm for designing nonlinear springs, or nonlinear dampers, using a mechanical force generator and its application to an aircraft landing gear
Yıldız, Fatih; Soylu, Reşit; Department of Mechanical Engineering (2021-12-03)
The landing gear system is one of the most critical aircraft sub-systems that takes part in the landing, taxi and take-off phases of every aircraft. Its main function is the absorption of part of aircraft's kinetic energy during landing. There are different types of shock absorbers to perform this task. The performance of the shock absorbers has developed a lot after the invention of air-oil type shock absorbers. However, increasing the performance of these shock absorber elements is still a field of resear...
A New method for the calculation of static flight loads of rigid fuselage of rotorcraft
Gül, Seyhan; Yaman, Yavuz; Department of Aerospace Engineering (2016)
The loads acting on a rotorcraft fuselage in pull-up, push-over, and yaw maneuvers and gust conditions are required to be calculated by civil and military standards. For each maneuver and the gust condition, different flight and rotor speeds, mass states, altitudes, and temperatures are required to be analyzed. This may add up to thousands of conditions. Calculation of fuselage loads for all these conditions with transient analysis is not only computationally expensive but it also requires a lot of engineer...
Effect of wing heating on flow structure of low swept delta wing
Şencan, Gizem; Yavuz, Mehmet Metin; Güvenç Yazıcıoğlu, Almıla; Department of Mechanical Engineering (2016)
Micro Air Vehicles (MAVs), Unmanned Air Vehicles (UAVs) and Unmanned Combat Air Vehicles (UCAVs), which can be represented by simplified planforms including low swept delta wings, have many advantages in defense industry and aeronautical field. Thus, the aerodynamics of nonslender delta wings including development and application of different flow control techniques have been of considerable interest in recent years. In this study, it is aimed to investigate the effect of heating on the flow structure over...
Citation Formats
IEEE
ACM
APA
CHICAGO
MLA
BibTeX
A. O. Yüksel, “Navier-Stokes computations of helicopter rotor flow fields,” M.S. - Master of Science, Middle East Technical University, 2017.