Investigation of rotor rotor interactions for two helicopters in forward flight using free vortex wake methodology

Date

2010-07-01

Author

Tonkal, Ozan Çağrı
Pehlivan, Sercan
Sezer Uzol, Nilay
İşler, Veysi

Metadata

Show full item record

Item Usage Stats

258
views

0
downloads

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 analyses are performed for 10 different positions of the rear rotor with respect to the front rotor. The wake of the front rotor, which is generated due to the mutual interactions of the wake and tip vortices, is significantly asymmetric and non-uniform. Therefore the rear rotor operates within a complex and vortical free-stream flow. The interaction of the incoming wake flow and the rear rotor generates a large, asymmetric wake region downstream of the rear rotor. The wake-rotor interactions cause substantial variations in the forces generated by the rear rotor. These variations also depend on the lateral location of the rear rotor with respect to the front one

Subject Keywords

Free flight, Stream flow, Vortex flow, Wakes

URI

http://arc.aiaa.org/doi/abs/10.2514/6.2010-4558
https://hdl.handle.net/11511/88254

DOI

https://doi.org/10.2514/6.2010-4558

Conference Name

AIAA 40th Fluid Dynamics Conference and Exhibit,( 28 Haziran - 01 Temmuz 2010)

Collections

Department of Aerospace Engineering, Conference / Seminar

Suggestions

OpenMETU
Core

Investigation of rotor wake interactions in helicopters using 3d unsteady free vortex wake methodology Yemenici, Öznur; Uzol, Oğuz; Department of Aerospace Engineering (2010) This thesis focuses on developing and examining the capabilities of a new in-house aerodynamic analysis tool, AeroSIM+, and investigating rotor-rotor aerodynamic interactions for two helicopters, one behind the other in forward flight. AeroSIM+ is a 3-D unsteady vortex panel method potential flow solver based on a free vortex wake methodology. Validation of the results with the experimental data is performed using the Caradonna-Tung hovering rotor test case. AeroSIM+ code is improved for forward flight cond...
Vortex Formation and Force Generation Mechanisms of the DelFly II in Hovering Flight Tenaglia, A; Perçin, Mustafa; Van Oudheusden, Bas W.; Deng, Shuanghou; Remes, Bart (2014-08-12) This paper addresses the unsteady aerodynamic mechanisms in the hovering flight of the DelFly II flapping-wing Micro Aerial Vehicle (MAV). Stereoscopic Particle Image Velocimetry (Stereo-PIV) were carried out around the wings at a high framing rate. Thrust-force was measured to investigate the relation between the vortex dynamics and the aerodynamic force generation. The results reveal that the Leading-Edge-Vortex (LEV), as well as the high flexibility of the wings, have a major effect on thrust generation....
Experimental investigation of tip anhedral effects on the aerodynamics of a model helicopter rotor in hover Uluocak, Sinem; Perçin, Mustafa; Uzol, Oğuz (2021-06-01) This study experimentally investigates the effects of tip anhedral on the rotor aerodynamic performance and the tip vortex characteristics in hovering flight. A five-bladed scaled helicopter rotor with blades that have either rectangular (baseline) or anhedral tip geometries was used as the experimental model. Thrust and torque measurements were performed at the tip Mach numbers (Mtip) of 0.3 and 0.4 at five different pitch angles. In addition, flow field measurements via phase-locked particle image velocim...
A Computational analysis on rotor-propeller arm interaction in hovering flight Yener, Serkan.; Perçin, Mustafa; Department of Aerospace Engineering (2019) This study presents a computational analysis on the interaction between rotor and different rotor frame-arm geometries in hovering flight. The influence of the frame arm on the aerodynamic performance of the rotor is assessed by using commercially available computational fluid dynamics (CFD) solver software ANSYS Inc. Fluent 17. Numerical results are validated for hovering and forward vertical climb flight conditions with thrust and torque measurements conducted on a 16x4 carbon fiber propeller. The thrust ...
Effects of mie vanes and tip injection on the performance and wake characteristics of HAWT Anik, Ezgi; Abdulrahim, Anas; Uzol, Oğuz (null; 2016-01-08) This paper presents the results of an experimental study that focuses on the tip leakage/vortex control of a model horizontal axis wind turbine rotor. The effects of Mie vanes and tip injection on the performance and wake characteristics of a model horizontal axis wind turbine rotor are investigated through experiments that are conducted by placing a specially designed three-bladed horizontal axis wind turbine rotor at the exit of an open-jet wind tunnel facility. The rotor blades are non-linearly twisted a...

Citation Formats

O. Ç. Tonkal, S. Pehlivan, N. Sezer Uzol, and V. İşler, “Investigation of rotor rotor interactions for two helicopters in forward flight using free vortex wake methodology,” presented at the AIAA 40th Fluid Dynamics Conference and Exhibit,( 28 Haziran - 01 Temmuz 2010), Chicago, Illinois, Amerika Birleşik Devletleri, 2010, Accessed: 00, 2021. [Online]. Available: http://arc.aiaa.org/doi/abs/10.2514/6.2010-4558.