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Journal articles on the topic 'Counter Rotating Propeller'

Author: Grafiati

Published: 3 June 2025

Last updated: 23 June 2025

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1

Xu, Jie, Jiaming Yu, Xinjiang Lu, Zhenkun Long, Yuteng Xu, and Hao Sun. "Aerodynamic Performance and Numerical Analysis of the Coaxial Contra-Rotating Propeller Lift System in eVTOL Vehicles." Mathematics 12, no. 7 (2024): 1056. http://dx.doi.org/10.3390/math12071056.

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Electric vertical takeoff and landing (eVTOL) vehicles possess high payload transportation capabilities and compact design features. The traditional method of increasing propeller size to cope with high payload is no longer applicable. Therefore, this study proposes the use of coaxial counter-rotating propellers as the lift system for eVTOL vehicles, consisting of two coaxially mounted, counter-rotating bi-blade propellers. However, if the lift of a single rotating propeller is linearly increased without considering the lift loss caused by the downwash airflow generated by the upper propeller and the torque effect of the lift system, it will significantly impact performance optimization and safety in the eVTOL vehicles design process. To address this issue, this study employed the Moving Reference Frame (MRF) method within Computational Fluid Dynamics (CFD) technology to simulate the lift system, conducting a detailed analysis of the impact of the upper propeller’s downwash flow on the aerodynamic performance of the lower propeller. In addition, the aerodynamic performance indicators of coaxial counter-rotating propellers were quantitatively analyzed under different speed conditions. The results indicated significant lift losses within the coaxial contra-rotating propeller system, which were particularly notable in the lift loss of the lower propeller. Moreover, the total torque decreased by more than 93.8%, and the torque was not completely offset; there was still a small torsional effect in the coaxial counter-rotating propellers. The virtual testing method of this study not only saves a significant amount of time and money but also serves as a vital reference in the design process of eVTOL vehicles.

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2

Hou, L. X., and A. K. Hu. "Spatial Fluctuating Pressure Calculation of Underwater Counter Rotating Propellers under Noncavitating Condition." International Journal of Rotating Machinery 2018 (2018): 1–12. http://dx.doi.org/10.1155/2018/2909546.

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The spatial fluctuating pressure field (FPF) of counter rotating propeller (CRP) under noncavitating condition is investigated. The hydrodynamic performance and pressure distributions on the blade surfaces are obtained through low-order potential-based panel method, which is also used to analyze the hydrodynamic interaction between the front and rear propellers of CRP as well as the hydrodynamic interference between any solid surface and propeller. The interaction between the given solid spherical surface and propeller is used to simulate the spatial FPF of propeller, and the fluctuating pressure induced by a propeller over one revolution is analyzed in frequency domain through fast Fourier transform. The method proposed is validated through two given propellers by comparing the calculation results with test data. The FPFs of the front and rear propellers are calculated and compared with that of the corresponding single propeller. The result shows that the CRP produces weaker FPF compared with the single propeller.

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3

Ma, Chengxiang, Liang Hong, and Haibin Chen. "Aerodynamic performance of coaxial counter-rotating propeller for air cushion ground effect wing vehicles." Journal of Physics: Conference Series 2977, no. 1 (2025): 012050. https://doi.org/10.1088/1742-6596/2977/1/012050.

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Abstract In the early stages of the design of an air cushion ground effect wing vehicle prototype, it is crucial to determine its power source. Compared with a single propeller, a coaxial counter-rotating propeller not only makes the torque uniform but also more efficient. Based on the STAR- CCM+ platform and slip grid model, the thrust and total thrust of the front/rear propellers under the conditions of the same rotational speed of coaxial counter-rotating propellers, different distances between propellers, and the same distances between propellers but different rotational speeds are simulated, respectively. The results show that the error between the simulated and experimental results of the aerodynamic characteristics of the single propeller in the model is within 7.4%, which proves the feasibility and applicability of the validated model. At the same rotational speed, the effect of distance on the total thrust is not significant, but the larger the distance, the smaller the interaction between the front and rear propellers and the more stable the output. At the same distance, the thrust increases with the increase of rotational speed. The optimum distance between the coaxial counter-rotating propellers of this air cushion ground effect wing vehicle was finally determined to be 0.35D and the optimum rotational speed was 4,800 rpm.

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4

Russo, Nicola, Aniello Daniele Marano, Giuseppe Maurizio Gagliardi, Michele Guida, Tiziano Polito, and Francesco Marulo. "Thrust and Noise Experimental Assessment on Counter-Rotating Coaxial Rotors." Aerospace 10, no. 6 (2023): 535. http://dx.doi.org/10.3390/aerospace10060535.

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Multirotors are gaining great importance in the layout of innovative and more agile mobility. In this framework, a possible solution to developing an aircraft complying with the stringent size requirements characterizing this type of application may be a coaxial rotor configuration. To exploit several possibilities linked to coaxial rotors, a scaled experimental model is designed to evaluate the performances of the counter-rotating propeller system, specifically regarding the distance between the two propellers. Both thrust and noise are considered as parameters of interest. Two brushless motors are deployed, whereas the propellers’ angular velocity, in terms of rounds per minute (rpm), is controlled by an external control system. Tests are conducted on both single isolated propellers as well as on the counter-rotating system: the two propellers and their respective motors are characterized regarding the thrust. Furthermore, a comparison with a numerical model is performed. Noise evaluation on the single propeller shows a motor contribution prevalence at a low rpm range (1140–1500 rpm) and a propeller prevalence for angular velocities higher than 1860 rpm. By varying the distances between the propellers, a sensitivity analysis is performed with the aim of identifying the optimum configuration, taking into account both noise and thrust performances.

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5

Poggi, Caterina, Giovanni Bernardini, Massimo Gennaretti, and Roberto Camussi. "Scalability of Mach Number Effects on Noise Emitted by Side-by-Side Propellers." Applied Sciences 12, no. 19 (2022): 9507. http://dx.doi.org/10.3390/app12199507.

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This paper presents a numerical investigation of noise radiated by two side-by-side propellers, suitable for Distributed-Electric-Propulsion concepts. The focus is on the assessment of the variation of the effects of blade tip Mach number on the radiated noise for variations of the direction of rotation, hub relative position, and the relative phase angle between the propeller blades. The aerodynamic analysis is performed through a potential-flow-based boundary integral formulation, which is able to model severe body–wake interactions.The noise field is evaluated through a boundary-integral formulation for the solution of the Ffowcs Williams and Hawkings equation. The numerical investigation shows that: the blade tip Mach number strongly affects the magnitude and directivity of the radiated noise; the increase of the tip-clearance increases the spatial frequency of the noise directivity at the two analyzed tip Mach numbers for both co-rotating and counter-rotating configurations; for counter-rotating propellers, the relative phase angle between the propeller blades provides a decrease of the averaged emitted noise, regardless the tip Mach number. One of the main results achieved is the scalability with the blade tip Mach number of the influence on the emitted noise of the considered design parameters.

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6

Cao, Mingzhi, Kun Liu, Chunqiang Wang, Jingbo Wei, and Zijie Qin. "Research on the Distributed Propeller Slipstream Effect of UAV Wing Based on the Actuator Disk Method." Drones 7, no. 9 (2023): 566. http://dx.doi.org/10.3390/drones7090566.

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Distributed electric propulsion technology has great potential and advantages in the development of drones. In this paper, to study the slipstream effect of distributed propellers, the actuator disk method was used to verify a single propeller, and the calculated thrust was in good agreement with the test results. Then, based on the actuator disk method, the influence of different installation positions on the slipstream effect was studied, and the distributed propeller layout was optimized by a genetic algorithm to improve the low-speed performance of the unmanned aerial vehicle (UAV) during the take-off phase and increase the cruise duration. The analysis results showed that the lift of the wing will be larger when the propellers are higher than the wing. The wing lift and drag of the counter-rotating are less than those of the co-rotating. Compared with the original layout, the lift coefficient of the optimized distributed propeller layout is significantly increased by 30.97%, while the lift/drag ratio is increased by 7.34%. Finally, we designed the test platform and qualitatively verified the calculated results without quantitative verification.

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7

Sharma, Sidharath, Guangyuan Huang, Stephen Ambrose, and Richard Jefferson-Loveday. "Numerical study on the aeroacoustics and interaction of two distributed-propulsion propellers in co- and counter-rotations." Journal of the Acoustical Society of America 152, no. 4 (2022): A52. http://dx.doi.org/10.1121/10.0015514.

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Driven by increasing demands for a sustainable and eco-friendly future in aviation, distributed electric propulsion (DEP) systems have received much attention for their high aerodynamic efficiency. DEP systems of lower noise emissions are desired by customers and policymakers and therefore it is important to understand the aeroacoustics and interaction of distributed propeller systems. In this paper, the aeroacoustics of a simplified DEP system is numerically investigated. The system consists of two Mejzlik 2-blade-9 × 9-inch propellers that are distributed side by side, with a tip-to-tip distance of 10 mm. Their rotating speed and freestream velocity are set as 6500 RPM and 12 m/s, respectively. The configurations of both co- and counter-rotation are considered. Compressible Large-eddy simulations are performed to obtain the flow solutions, and the Ffowcs Williams and Hawkings (FW-H) method is used to calculate the corresponding far-field acoustic solutions. The results present interaction effects for both configurations and compare against isolated propeller results. First, the thrust and the induced sound of each propeller are examined and secondly the impact of the interaction effects on the aerodynamic and acoustic performance is investigated. Finally, sound interference in the acoustic fields is assessed and compared for both co- and counter-rotation configurations.

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8

Korkan, K. D., and J. A. Gazzaniga. "Off-design analysis of counter-rotating propeller configurations." Journal of Propulsion and Power 3, no. 1 (1987): 91–93. http://dx.doi.org/10.2514/3.22958.

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9

Loginov, Vasyl, Yevgen Ukrainets, Viktor Popov, and Yevgen Spirkin. "Determining the Aerodynamic Characteristics of a Propeller-Driven Anti-UAV Fighter While Designing Air Propellers." Transactions on Aerospace Research 2021, no. 4 (2021): 53–67. http://dx.doi.org/10.2478/tar-2021-0023.

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Abstract Given the rising importance of unmanned aerial vehicles (UAVs), this article addresses the urgent scientific problem of determining the aerodynamic characteristics of a UAV while laying out the propellers for the wings. We discuss the methodology for experimental wind-tunnel studies of aircraft configurations with propellers. It is shown that a characteristic feature of the configuration small-elongation wing with propellers is the absence of elements that are not affected by propellers. This feature makes it difficult to implement and automate a wind tunnel experiment, since there are problems with providing similar criteria for a working propeller; it is difficult to achieve perfect balancing for solid drive propellers, which causes vibration, the level of which depends on uncontrolled factors; the inability to neglect the presence of the body elements influence to the blades of propellers; the difficulty of direct measuring propeller thrust and torque. The presented methodology involves the integrated usage of experimental and numerical methods to eliminate the difficulties in conducting physical experiments in a wind tunnel. This approach makes it possible to combine the high credibility of experimental data in the study of the physical essence of phenomena with high efficiency and accuracy in determining aerodynamic characteristics by numerical methods. Using this approach, we established dependences of the aerodynamic characteristics of the small-elongation wing configuration with counter-rotating propellers on the geometric and kinematic parameters of the configuration for other extensions and constrictions of the wings. These data can serve as the basis for the development of recommendations for the selection of sensible geometric parameters of the aerodynamic configuration of a small-elongation wing with counter-rotating propellers.

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10

Wang, Hanyi, Peng Shan, and Yicheng Zhou. "Development and Application of Open Rotor Discrete Noise Prediction Program Using Time-Domain Methods." Applied Sciences 14, no. 3 (2024): 1138. http://dx.doi.org/10.3390/app14031138.

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The aerodynamic noise of an open rotor is one of the critical challenges that must be considered in its design and application. FODNOPP, a program specifically programmed to predict the aerodynamic discrete noise of single- and counter-rotating open rotors (such as propellers, propfans, and rotorcraft rotors) at subsonic, transonic, and supersonic helical blade tip speeds, has recently been developed by the first author. This program is composed of four prediction codes, namely code a1, code a2, code b, and code c, each based on Farassat-derived formulations Formu 1-RTE, Formu 1A, Formu 1-Sph, and Formu 3, providing time-domain solutions to the Ffowcs Williams–Hawkings equation. Four verification examples for both propeller low-speed flight noise and counter-rotating propfan take-off noise are presented, along with an application case for transonic helical tip speed counter-rotating propfan cruise noise. The results demonstrate the accuracy of FODNOPP in calculating the noise for these verification cases. And in the counter-rotating propfan cruise noise case, the maximum harmonic sound pressure level of the rear propfan is 5.5 dB higher than that of the front propfan. FODNOPP can be referred to as a comprehensive design tool, and it offers valuable guidance for engineering design focused on rotor-related noise reduction.

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11

Nagel, R. T., and H. V. L. Patrick. "Aerodynamic interaction tones of a model counter-rotating propeller." AIAA Journal 26, no. 4 (1988): 498–500. http://dx.doi.org/10.2514/3.9923.

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12

De Paola, Elisa, Alessandro Di Marco, Luana Georgiana Stoica, Leonardo Falcini, and Roberto Camussi. "Experimental investigation on a side-by-side twin rotor system in pusher configuration." INTER-NOISE and NOISE-CON Congress and Conference Proceedings 265, no. 2 (2023): 5862–72. http://dx.doi.org/10.3397/in_2022_0870.

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Growing interest in electric propulsion, together with the increased deployment of unmanned aerial vehicles, results in the consequent need for a clear understanding of the physical phenomena under propeller interactions which represent a primary noise source in multi-rotor configurations. To this purpose, the effect of rotor-to-rotor interactions of a twin pusher propeller configuration at static thrust conditions was experimentally investigated through aerodynamic and aeroacoustic measurement campaigns. The propellers tested refer to the APC-8x45MR rotor with an 8 inches diameter. The aerodynamics and aeroacoustics of several configurations were investigated using PIV technique, Pitot tube acquisitions, and microphone measurements performed in an anechoic environment. The propeller speed was varied within a typical range in the applications for both co-rotating and counter-rotating layouts. To define critical relative positions, many tip-to-tip separation distances were considered highlighting the general effects. Owing to the deformation exhibited by the rotor wakes due to their proximity, the pressure and velocity signals were conditioned to inspect the driving mechanisms responsible for the noise emission. Results provide a deeper insight into the physics involved and show different types of interaction effects on the fluid-dynamic field as a function of the propeller position, allowing the identification of the main critical configurations.

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13

Kobayakawa, Makoto, and Masahiro Nakao. "Numerical solutions for the flowfield around a counter-rotating propeller." Journal of Aircraft 26, no. 5 (1989): 417–22. http://dx.doi.org/10.2514/3.45779.

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14

Dudnikov, S. Yu, P. N. Kuznetsov, and A. I. Mel’nikova. "Research of Ducted Propellers. Comparison of Coaxial, Four Bladed, and Eight-Bladed Counter-Rotating Propeller." Russian Aeronautics 66, no. 2 (2023): 259–66. http://dx.doi.org/10.3103/s1068799823020095.

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15

McCurdy, David A. "Advanced turboprop aircraft flyover noise: Annoyance to counter‐rotating‐propeller configurations." Journal of the Acoustical Society of America 83, S1 (1988): S114. http://dx.doi.org/10.1121/1.2025159.

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16

Littik, Y. Fredrika, Y. Heru Irawan, and M. Agung Bramantya. "Flow-driven simulation on variation diameter of counter rotating wind turbines rotor." MATEC Web of Conferences 154 (2018): 01111. http://dx.doi.org/10.1051/matecconf/201815401111.

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Wind turbines model in this paper developed from horizontal axis wind turbine propeller with single rotor (HAWT). This research aims to investigating the influence of front rotor diameter variation (D1) with rear rotor (D2) to the angular velocity optimal (ω) and tip speed ratio (TSR) on counter rotating wind turbines (CRWT). The method used transient 3D simulation with computational fluid dynamics (CFD) to perform the aerodynamics characteristic of rotor wind turbines. The counter rotating wind turbines (CRWT) is designed with front rotor diameter of 0.23 m and rear rotor diameter of 0.40 m. In this research, the wind velocity is 4.2 m/s and variation ratio between front rotor and rear rotor (D1/D2) are 0.65; 0.80; 1.20; 1.40; and 1.60 with axial distance (Z/D2) 0.20 m. The result of this research indicated that the variation diameter on front rotor influence the aerodynamics performance of counter rotating wind turbines.

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17

MURAKAMI, Tengen, Pin LIU, and Toshiaki KANEMOTO. "Posture Stabilization of Floating Counter-rotating Propeller Type Tidal Stream Power Unit." Proceedings of the Fluids engineering conference 2020 (2020): OS09–17. http://dx.doi.org/10.1299/jsmefed.2020.os09-17.

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18

Lyu, Wei-Liang, and Guo-Hua Xu. "Interactional Effect of Propulsive Propeller Location on Counter-Rotating Coaxial Main Rotor." Journal of Aircraft 55, no. 6 (2018): 2538–45. http://dx.doi.org/10.2514/1.c033316.

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19

Kim, Soo-Jung, Tae-Young Yeom, and Seungbae Lee. "A Study on Thrust Performance of Counter-Rotating Biomimetic Propeller System for a Manned Drone." KSFM Journal of Fluid Machinery 24, no. 1 (2021): 41–46. http://dx.doi.org/10.5293/kfma.2021.24.1.041.

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20

Pearson, K. J., Keith Horne, and Warren Skidmore. "Fireballs, Flares and Flickering." International Astronomical Union Colloquium 190 (2004): 279–92. http://dx.doi.org/10.1017/s0252921100002220.

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AbstractWe review our understanding of the prototype “Propeller” system AE Aqr and we examine its flaring behaviour in detail. The flares are thought to arise from collisions between high density regions in the material expelled from the system after interaction with the rapidly rotating magnetosphere of the white dwarf. We show calculations of the time-dependent emergent optical spectra from the resulting hot, expanding ball of gas and derive values for the mass, lengthscale and temperature of the material involved. We see that the fits suggest that the secondary star in this system has reduced metal abundances and that, counter-intuitively, the evolution of the fireballs is best modelled as isothermal.

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21

GARRETT, S. J., Z. HUSSAIN, and S. O. STEPHEN. "The cross-flow instability of the boundary layer on a rotating cone." Journal of Fluid Mechanics 622 (March 10, 2009): 209–32. http://dx.doi.org/10.1017/s0022112008005181.

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Experimental studies have shown that the boundary-layer flow over a rotating cone is susceptible to cross-flow and centrifugal instability modes of spiral nature, depending on the cone sharpness. For half-angles (ψ) ranging from propeller nose cones to rotating disks (ψ ≥ 40°), the instability triggers co-rotating vortices, whereas for sharp spinning missiles (ψ < 40°), counter-rotating vortices are observed. In this paper we provide a mathematical description of the onset of co-rotating vortices for a family of cones rotating in quiescent fluid, with a view towards explaining the effect of ψ on the underlying transition of dominant instability. We investigate the stability of inviscid cross-flow modes (type I) as well as modes which arise from a viscous–Coriolis force balance (type II), using numerical and asymptotic methods. The influence of ψ on the number and orientation of the spiral vortices is examined, with comparisons drawn between our two distinct methods as well as with previous experimental studies. Our results indicate that increasing ψ has a stabilizing effect on both the type I and type II modes. Favourable agreement is obtained between the numerical and asymptotic methods presented here and existing experimental results for ψ > 40°. Below this half-angle we suggest that an alternative instability mechanism is at work, which is not amenable to investigation using the formulation presented here.

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22

Paterson, Eric G., and Fred Stern. "Computation of Unsteady Viscous Marine-Propulsor Blade Flows—Part 2: Parametric Study." Journal of Fluids Engineering 121, no. 1 (1999): 139–47. http://dx.doi.org/10.1115/1.2821994.

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In this two-part paper, time-accurate solutions of the Reynolds-averaged Navier-Stokes equations are presented, which address through model problems, the response of turbulent propeller-blade boundary layers and wakes to external-flow traveling waves. In Part 1, the Massachusetts Institute of Technology flapping-foil experiment was simulated and the results validated through comparisons with data. The response was shown to be significantly more complex than classical unsteady boundary layer and unsteady lifting flows thus motivating further study. In Part 2, the effects of frequency, waveform, and foil geometry are investigated. The results demonstrate that uniquely different response occurs for low and high frequency. High-frequency response agrees with behavior seen in the flapping-foil experiment, whereas low-frequency response displays a temporal behavior which more closely agrees with classical inviscid-flow theories. Study of waveform and geometry show that, for high frequency, the driving mechanism of the response is a viscous-inviscid interaction created by a near-wake peak in the displacement thickness which, in turn, is directly related to unsteady lift and the oscillatory wake sheet. Pressure waves radiate upstream and downstream of the displacement thickness peak for high frequency flows. Secondary effects, which are primarily due to geometry, include gust deformation due to steady-unsteady interaction and trailing-edge counter-rotating vortices which create a two-layered amplitude and phase-angle profile across the boundary layer.

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23

Hanson, Donald B. "Noise of counter-rotation propellers." Journal of Aircraft 22, no. 7 (1985): 609–17. http://dx.doi.org/10.2514/3.45173.

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24

Liu, Pin, Fumiha Odo, Tengen Murakami, and Toshiaki Kanemoto. "Acoustic noise measurement in counter-rotating propellers." Journal of Mechanical Science and Technology 33, no. 7 (2019): 3187–92. http://dx.doi.org/10.1007/s12206-019-0613-6.

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25

Shahimi, Sharis-Shazzali, Nur Azam Abdullah, Ameen Topa, Meftah Hrairi, and Ahmad Faris Ismail. "NUMERICAL MODELLING OF BIRD STRIKE ON A ROTATING ENGINE BLADES BASED ON VARIATIONS OF POROSITY DENSITY." IIUM Engineering Journal 23, no. 1 (2022): 412–23. http://dx.doi.org/10.31436/iiumej.v23i1.2146.

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A numerical investigation is conducted on a rotating engine blade subjected to a bird strike impact. The bird strike is numerically modelled as a cylindrical gelatine with hemispherical ends to simulate impact on a rotating engine blade. Numerical modelling of a rotating engine blade has shown that bird strikes can severely damage an engine blade, especially as the engine blade rotates, as the rotation causes initial stresses on the root of the engine blade. This paper presents a numerical modelling of the engine blades subjected to bird strike with porosity implemented on the engine blades to investigate further damage assessment due to this porosity effect. As porosity influences the decibel levels on a propeller blade or engine blade, the damage due to bird strikes can investigate the compromise this effect has on the structural integrity of the engine blades. This paper utilizes a bird strike simulation through an LS-Dyna Pre-post software. The numerical constitutive relations are keyed into the keyword manager where the bird’s SPH density, a 10 ms simulation time, and bird velocity of 100 m/s are all set. The blade rotates counter-clockwise at 200 rad/s with a tetrahedron mesh. The porous regions or voids along the blade are featured as 5 mm diameter voids, each spaced 5 mm apart. The bird is modelled as an Elastic-Plastic-Hydrodynamic material model to analyze the bird’s fluid behavior through a polynomial equation of state. To simulate the fluid structure interaction, the blade is modelled with Johnson-Cook Material model parameters of aluminium where the damage of the impact can be observed. The observations presented are compared to previous study of a bird strike impact on non-porous engine blades. ABSTRAK: Penyelidikan berangka telah dijalankan ke atas bilah enjin berputar tertakluk kepada impak pelanggaran burung. Pelanggaran burung tersebut telah dimodelkan secara berangka sebagai silinder gelatin dengan hujungnya berbentuk hemisfera demi mensimulasikan impaknya ke atas bilah enjin yang berputar. Pemodelan berangka bilah-bilah enjin yang berputar tersebut menunjukkan bahawa pelanggaran burung mampu menyebabkan kerosakan teruk terhadap bilah enjin terutamanya apabila bilah enjin sedang berputar oleh sebab putaran menghasilkan tekanan asal di pangkal bilah enjin. Kajian ini mengetengahkan pemodelan berangka ke atas bilah-bilah enjin tertakluk kepada pelanggaran burung terhadap bilah-bilah enjin yg mempunyai keliangan demi menyelidik dan menilai kerosakan kesan daripada keliangan tersebut. Keliangan juga mempengaruhi tahap-tahap desibel ke atas bilah kipas ataupun bilah enjin, kerosakan hasil serangan burung boleh menterjemah tahap ketahanan struktur integriti bagi bilah-bilah enjin tersebut. Penyelidikan ini mengguna pakai perisian “LS-Dyna Pre-post” untuk simulasi pelanggaran burung. Hubungan konstitutif berangka telah dimasukkan sebagai kata kunci di mana ketumpatan SPH burung, masa simulasi 10ms, dan halaju burung ditetapkan kepada 100 m/s. Bilah tersebut berputar pada 200 rad/s arah lawan jam dengan jejaring tetrahedron. Kawasan berliang atau kosong di sepanjang bilah ditetapkan diameternya kepada 5 mm, dan dijarakkan 5 mm di antara satu sama lain. Burung pula dimodelkan sebagai material “Elastic-Plastic-Hydrodynamic” untuk mengkaji sifat bendalir burung melalui persamaan polinomial. Demi mensimulasi interaksi struktur bendalir, bilah tersebut dimodelkan sebagai parameter aluminium material “Johnson Cook” di mana kerosakan daripada impak tersebut dapat diteliti. Penelitian-penelitian tersebut dibandingkan dengan kajian terdahulu ke atas serangan burung terhadap bilah-bilah enjin tidak berliang.

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Tam, C. K. W., M. Salikuddin, and D. B. Hanson. "Acoustic interference of counter-rotation propellers." Journal of Sound and Vibration 124, no. 2 (1988): 357–66. http://dx.doi.org/10.1016/s0022-460x(88)80193-7.

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27

FREY, Kevin, Gen ENDO, and Edwardo F. FUKUSHIMA. "2P1-I09 Design of an Underactuated Underwater Vehicle Using Counter Rotating Propellers(Underwater Robot and Mechatronics(2))." Proceedings of JSME annual Conference on Robotics and Mechatronics (Robomec) 2012 (2012): _2P1—I09_1—_2P1—I09_2. http://dx.doi.org/10.1299/jsmermd.2012._2p1-i09_1.

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28

Fujii, S., H. Nishiwaki, and K. Takeda. "Noise and performance of a counter-rotation propeller." Journal of Aircraft 23, no. 9 (1986): 719–24. http://dx.doi.org/10.2514/3.45367.

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29

Chen, Yaxi, Peiqing Liu, Zhihao Tang, and Hao Guo. "Wind tunnel tests of stratospheric airship counter rotating propellers." Theoretical and Applied Mechanics Letters 5, no. 1 (2015): 58–61. http://dx.doi.org/10.1016/j.taml.2015.01.001.

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30

Tang, Zhihao, Peiqing Liu, Yaxi Chen, and Hao Guo. "Experimental Study of Counter-Rotating Propellers for High-Altitude Airships." Journal of Propulsion and Power 31, no. 5 (2015): 1491–96. http://dx.doi.org/10.2514/1.b35746.

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31

Güngör, E., and İ. B. Özdemir. "Prediction of Noise and Acoustical Spectrum of Counter-Rotating Propellers." Journal of Ship Research 62, no. 3 (2018): 166–82. http://dx.doi.org/10.5957/josr.170050.

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32

Srivastava, R., and Lakshmi N. Sankar. "Efficient hybrid scheme for the analysis of counter-rotating propellers." Journal of Propulsion and Power 9, no. 3 (1993): 382–88. http://dx.doi.org/10.2514/3.23633.

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Lee, Nak-Joong, Morihito Inagaki, and Toshiaki Kanemoto. "Performance of counter-rotating tandem propellers at oblique flow conditions." IOP Conference Series: Earth and Environmental Science 240 (March 27, 2019): 052004. http://dx.doi.org/10.1088/1755-1315/240/5/052004.

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34

Brizzolara, Stefano, Davide Grassi, and Emilio P. Tincani. "Design Method for Contra-Rotating Propellers for High-Speed Crafts: Revising the Original Lerbs Theory in a Modern Perspective." International Journal of Rotating Machinery 2012 (2012): 1–18. http://dx.doi.org/10.1155/2012/408135.

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The main theoretical and numerical aspects of a design method for optimum contrar-rotating (CR) propellers for fast marine crafts are presented. We propose a reformulated version of a well-known design theory for contra-rotating propellers, by taking advantage of a new fully numerical algorithm for the calculation of the mutually induced velocities and introducing new features such as numerical lifting surface corrections, use of an integrated modern cavitation/strength criteria, a modified method to consider different numbers of blades among the two propellers, and to allow for an unloading function in the search for the optimal circulation distribution. The paper first introduces the main theoretical principles of the new methods and then discusses the influence of the main design parameters on an emblematic example of application in the case of counter rotating propellers for a pod propulsor designed for fast planing crafts (35 knots and above).

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35

Hanson, D. B., and C. J. McColgan. "Noise of counter-rotation propellers with nonsynchronous rotors." Journal of Aircraft 22, no. 12 (1985): 1097–99. http://dx.doi.org/10.2514/3.45256.

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36

Hanson, D. B., and C. J. McColgan. "Errata: Noise of Counter-rotation Propellers with Nonsynchronous Rotors." Journal of Aircraft 23, no. 7 (1986): 608. http://dx.doi.org/10.2514/3.56775.

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37

Block, P. J. W. "Noise radiation patterns of counter-rotation and unsteadily loaded single-rotation propellers." Journal of Aircraft 22, no. 9 (1985): 776–83. http://dx.doi.org/10.2514/3.45201.

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38

Playle, S. C., K. D. Korkan, and E. von Lavante. "A numerical method for the design and analysis of counter-rotating propellers." Journal of Propulsion and Power 2, no. 1 (1986): 57–63. http://dx.doi.org/10.2514/3.22845.

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39

Funami, Yuki, Yuji Nakanishi, Nak-Joong Lee, Bin Huang, and Toshiaki Kanemoto. "Counter-Rotating Type Horizontal-Axis Bidirectional Propellers for Tidal Stream Power Unit." Journal of Power and Energy Engineering 05, no. 07 (2017): 34–44. http://dx.doi.org/10.4236/jpee.2017.57003.

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40

Nakanishi, Y., Y. Funami, and T. Yano. "Motion analysis of a power unit moored with a cable for tidal power generation (2D calculation considering fluid forces acting on the unit and cable)." Journal of Physics: Conference Series 2217, no. 1 (2022): 012037. http://dx.doi.org/10.1088/1742-6596/2217/1/012037.

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Abstract The power unit with counter-rotating propellors has been proposed for a tidal power generation. The unit has the potential to be moored with a cable because of inherent equilibrium of the rotational moments acting on the counter-rotating propellors. On the other hand, the flow condition of a tidal current is not steady, therefore, the motion and the posture of the power unit should be investigated for the stability of the power generation in terms of the fluid dynamics. In this study, the two-dimensional motion of the power unit and the cable modelled with rigid elements connected each other with pivots are analyzed as the combination of translational and rotational motions with the constraint of the connected elements. The time-dependent position, angle and relative velocity of each calculation element were obtained to validate the usefulness of the proposed method.

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RICO, Jose A. SILVA, Andre Y. YASUTOMI, and Edwardo F. FUKUSHIMA. "2A2-M06 Study of Underactuated Underwater Vehicle Using Counter Rotating Propellers : 2nd Report:Basic Experiments and Model Parameter Estimation(Underwater Robot and Mechatronics)." Proceedings of JSME annual Conference on Robotics and Mechatronics (Robomec) 2013 (2013): _2A2—M06_1—_2A2—M06_2. http://dx.doi.org/10.1299/jsmermd.2013._2a2-m06_1.

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Lee, Young-Kyun, Tae-Young Yeom, and Seungbae Lee. "A Study on Noise Analysis of Counter-Rotating Propellers for a Manned Drone." KSFM Journal of Fluid Machinery 25, no. 2 (2022): 38–44. http://dx.doi.org/10.5293/kfma.2022.25.2.038.

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43

Grassi, Davide, Stefano Brizzolara, Michele Viviani, Luca Savio, and Sara Caviglia. "Design and analysis of counter-rotating propellers-comparison of numerical and experimental results." Journal of Hydrodynamics 22, S1 (2010): 553–59. http://dx.doi.org/10.1016/s1001-6058(09)60254-7.

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44

Kutt, Filip, Krzysztof Blecharz, and Dariusz Karkosiński. "Axial-Flux Permanent-Magnet Dual-Rotor Generator for a Counter-Rotating Wind Turbine." Energies 13, no. 11 (2020): 2833. http://dx.doi.org/10.3390/en13112833.

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Coaxial counter-rotating propellers have been widely applied in ships and helicopters for improving the propulsion efficiency and offsetting system reactive torques. Lately, the counter-rotating concept has been introduced into the wind turbine design. Distributed wind power generation systems often require a novel approach in generator design. In this paper, prototype development of axial-flux generator with a counter-rotating field and armature is presented. The design process was composed of three main steps: analytical calculation, FEM simulation and prototype experimental measurements. The key aspect in the prototype development was the mechanical construction of two rotating components of the generator. Sturdy construction was achieved using two points of contact between both rotors via the placement of the bearing between the inner and outer rotor. The experimental analysis of the prototype generator has been conducted in the laboratory at the dynamometer test stand equipped with a torque sensor. The general premise for the development of such a machine was an investigation into the possibility of developing a dual rotor wind turbine. The proposed solution had to meet certain criteria such as relatively simple construction of the generator and the direct coupling between the generator and the wind turbines. The simple construction and the lack of any gearbox would allow for such a system to be constructed relatively cheaply, which is a key aspect in further system development.

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Alves Pereira, Francisco, Alessandro Capone, and Fabio Di Felice. "Flow field and vortex interactions in the near wake of two counter-rotating propellers." Applied Ocean Research 117 (December 2021): 102918. http://dx.doi.org/10.1016/j.apor.2021.102918.

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KOBAYAKAWA, Makoto, and Masahiro NAKAO. "Numerical solutions of the Euler equations for the flow field around counter-rotating propellers." Journal of the Japan Society for Aeronautical and Space Sciences 35, no. 403 (1987): 389–98. http://dx.doi.org/10.2322/jjsass1969.35.389.

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Capone, Alessandro, Fabio Di Felice, and Francisco Alves Pereira. "On the flow field induced by two counter-rotating propellers at varying load conditions." Ocean Engineering 221 (February 2021): 108322. http://dx.doi.org/10.1016/j.oceaneng.2020.108322.

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48

Shi, W. K., L. J. Li, D. T. Qin, and T. C. Lim. "Analysis of power flow in a counter-rotating epicyclic gearing for electrical propulsion system." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 225, no. 12 (2011): 2973–80. http://dx.doi.org/10.1177/0954406211411548.

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A novel compound epicyclic gearing that combines a planetary gear train with a differential gear train is designed for an electrical propulsion system of underwater unmanned vehicles. This epicyclic gearing can transform a single input into two counter-rotating outputs with equal torque amplitudes and speeds. Based on the analysis method of power flow in the differential gear train, the character of the power flow of the compound epicyclic gearing was determined. After comparing with the power distribution of input flow, the condition of this mechanism without power recirculation was investigated. Because the reactive torque of the motor stator is balanced by the torque on ring gear of planetary gear train, no net torque acts on the vessel being propelled.

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49

Liu, P., H. Jung, T. Murakami, and T. Kanemoto. "Scale effect and undersea noise of counter-rotating propellers installed in tidal stream power unit." IOP Conference Series: Earth and Environmental Science 163 (July 30, 2018): 012043. http://dx.doi.org/10.1088/1755-1315/163/1/012043.

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50

De Gregorio, F., P. Candeloro, G. Ceglia, and T. Pagliaroli. "Flow field and acoustic assessment of twin rotors in hover conditions." Journal of Physics: Conference Series 2802, no. 1 (2024): 012011. http://dx.doi.org/10.1088/1742-6596/2802/1/012011.

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Abstract The paper presents part of the experimental activities in the GARTEUR Action Group RC/AG-26 framework to study the acoustic and aerodynamic characteristics of small rotors, including the influence of the rotor-rotor interactions. Two rotors with three-bladed propellers with a diameter D=393.7 mm were tested at a constant rotational speed of 5200 RPM, for different rotating verses and geometry configurations. Two rotor configurations were assessed in hover, i.e., either a baseline comprised of one isolated rotor, or two rotors arranged side-by-side. The aerodynamic loads, flow field velocity and acoustics emissions, were investigated using a six-component load cell, Particle Image Velocimetry and microphone array measurements, respectively. The aerodynamic characterisation of the isolated rotor was performed for a variety of rotating speeds. The interference between the slipstreams due to the side-by-side rotors was studied for co-rotating and counter-rotating verses at distances between the rotor axes of d=1.02D, d=1.1D, and 1.2D. The results showed that the slipstreams of the side-by-side rotors deflect and vary with the inter-axial distance. The rotor-rotor interaction, which is found to be related to the rotor distance, affects also the acoustic emissions. A remarkable loss of thrust is observed for the closest distance d=1.02D. Regarding acoustic emissions, the overall sound pressure level increases as the rotors run in counter-rotating verses compared to the co-rotating.

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