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
Main Rotor - Tail Rotor Interactional Noise
Date
2019-10-30
Author
Atalay, Mehmet Melih
Şenipek, Murat
Yücekayalı, Arda
Özyörük, Yusuf
Metadata
Show full item record
Item Usage Stats
202
views
0
downloads
Cite This
In this paper, effects of main rotor – tail rotor interactions on noise characteristics are investigated for a typical 10 ton class helicopter. Evaluations are performed at hover and quartering flight conditions with top-forward, topforward with 10o of cant angle, and bottom-forward configurations. Isolated tail rotor analyses are also carried out for interaction off conditions for comparison purposes. Main-tail rotor combined full helicopter trim calculations are done for interaction on conditions using CHARM, providing time-dependent pressure and blade position data, and then aerodynamic noise signatures are computed with in-house acoustic code, TACO, Interaction effects on the blade loads and performance are investigated, and acoustic signatures at various observer locations are estimated and compared for hover and quartering flight condition.
URI
https://hdl.handle.net/11511/71925
Conference Name
8th Asian/Australian Rotorcraft Forum (30 Ekim - 02 Kasım 2019)
Collections
Department of Aerospace Engineering, Conference / Seminar
Suggestions
OpenMETU
Core
Investigation of rotor rotor interactions for two helicopters in forward flight using free vortex wake methodology
Tonkal, Ozan Çağrı; Pehlivan, Sercan; Sezer Uzol, Nilay; İşler, Veysi (null; 2010-07-01)
This paper presents an investigation of the aerodynamic interactions between two UH-1H helicopter rotors in forward flight. The wake flow structure and performance characteristics of the rotors are investigated when the rear rotor is operating within the wake of the front rotor. A 3-D unsteady vortex-panel method potential flow solver based on a free-vortex-wake methodology is used for this purpose. The solver is validated using the experimental data from the Caradonna-Tung experiments. The interactional an...
Genetic Algorithm based aerodynamic shape optimization tool for wind turbine blades and its implementation to helicopter blades
Polat, Özge; Sezer-uzol, Nilay; Tuncer, İsmail Hakkı (2014-01-01)
This study presents a methodology first built up for the aerodynamic shape optimization for wind turbine rotors and its modified version for a helicopter rotor in hover. The Genetic Algorithm (GA) coupled with an in-house Blade Element Momentum (BEM) tool is used in the design optimization process. The wind turbine blade optimization studies are performed for maximizing the power production at a given wind speed, rotor speed and rotor diameter, while for the helicopter blade optimization in hover, figure of...
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...
Experimental investigation of the helicopter blade tip shape effects on aerodynamic performance and tip vortex characteristics
Uluocak, Sinem; Perçin, Mustafa; Uzol, Oğuz; Department of Aerospace Engineering (2019)
This study experimentally investigates the effects of different rotor blade tip shapes on the rotor aerodynamic performance and the tip vortex characteristics in hovering flight. Force, torque and flow field measurements were performed on a 1.3 m diameter 5-bladed model rotor for four different blades: rectangular (RECT), anhedral (ANHD), tapered-swept (TAPER) and tapered-swept-anhedral (TSA). Thrust and torque measurements show that all tip modifications have a positive effect on the aerodynamic performance wh...
Flight test maneuver design and aerodynamic parameter estimation for single use autonomous air vehicles
Vefa Yavuzturk, N.; Topbas, Eren; Yazıcıoğlu, Yiğit (null; 2017-01-01)
In this paper, a maneuver design and aerodynamic parameter estimation procedure is carried out for single use autonomous gliding air vehicles where allowable flight testing time is limited. At first, using the priori aerodynamics of a gliding vehicle, an aerodynamic model has been built and six degree of freedom simulation tool is generated. This priori aerodynamic knowledge is used to design a multi-sine input to excite the system at predetermined flight conditions during flight test. Afterwards, using the...
Citation Formats
IEEE
ACM
APA
CHICAGO
MLA
BibTeX
M. M. Atalay, M. Şenipek, A. Yücekayalı, and Y. Özyörük, “Main Rotor - Tail Rotor Interactional Noise,” presented at the 8th Asian/Australian Rotorcraft Forum (30 Ekim - 02 Kasım 2019), Ankara, Türkiye, 2019, Accessed: 00, 2021. [Online]. Available: https://hdl.handle.net/11511/71925.
