Relevant bibliographies by topics / Counter Rotating Propeller

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers

Academic literature on the topic 'Counter Rotating Propeller'

Author: Grafiati
Published: 3 June 2025
Last updated: 23 June 2025

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Journal articles on the topic "Counter Rotating Propeller"

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 The traditional method of increasing propeller size to cope with high payload is no longer applicable.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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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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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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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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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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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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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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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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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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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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Dissertations / Theses on the topic "Counter Rotating Propeller"

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Parry, Anthony Brian. "Theoretical prediction of counter-rotating propeller noise." Thesis, University of Leeds, 1988. http://etheses.whiterose.ac.uk/319/.

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A theoretical prediction scheme has been developed for the tone noise generated by a counter-rotation propeller. We start by deriving formulae for the harmonic components of the far acoustic field generated by the thickness and steady loading noise sources. Excellent agreement is shown between theory and measurements. Asymptotic approximation techniques are described which enable us to simplify considerably the complex radiation formulae, whilst retaining all of their important characteristics, and thus save, typically, 95% of computer processing time. Next we derive formulae for the radiated sound field generated by aerodynamic interactions between the blade rows. Here, however, the inputs to the formulae include a knowledge of the fluctuating blade pressure fields which cannot generally be assumed given and must therefore be calculated within the prediction scheme. In the case of viscous wake interactions we consider various models for the wake profile which is written as a series of harmonic gusts. The fluctuating pressure distribution on the downstream blades can then be calculated in the high frequency limit. Comparisons are made between measurements and predictions for a counter-rotation propeller and for rotor/stator interaction on a model fan rig. For potential field interactions we describe the flow fields due to blade circulation and blade thickness in terms of harmonic gusts with the flow assumed incompressible. The blade response is calculated for both finite and semi-infinite airfoils. Some important differences between these two cases are noted in both high and low frequency limits. Predicted noise levels are much improved over those obtained using only the viscous wake model. The inclusion of compressibility, in both flow field and airfoil response calculations, provides a further improvement in the predicted noise levels. The discrepancy between measurements and predictions at this stage is, typically, 2 or 3 dB.
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Jacobson, Jessica. "Using Single Propeller Performance Data to Predict Counter-Rotating Propeller Performance for a High Speed Autonomous Underwater Vehicle." Thesis, Virginia Tech, 2007. http://hdl.handle.net/10919/32753.

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The use of counter-rotating propellers is often desirable for aerospace and ocean engineering applications. Counter-rotating propellers offer higher peak efficiencies, better off-design performance, and roll control capabilities. But counter-rotating propeller matching is a difficult and complex procedure. Although much research has been done on the design of optimal counter-rotating propeller sets, there has been less focus on predicting the performance of unmatched counter-rotating sets. In this study, it was desired to use off-the-shelf marine propellers to make a counter-rotating pair for a high speed autonomous underwater vehicle (AUV). Counter-rotating propellers were needed to provide roll control for the AUV. Pre-existing counter-rotating propeller design methods were not applicable because they all require inputs of complex propeller blade geometries. These geometries are rarely known for off-the-shelf propellers. <p> This study proposes a new method for predicting the counter-rotating performance of unmatched propeller sets. It is suggested here that propeller performance curves can be used to predict counter-rotating thrust and torque performance. <p> Propeller performance tests were run in the Virginia Tech Water Tunnel for a variety of small, off-the shelf propellers. The collected data was used to generate the propeller performance curves. The propellers were then paired up and tested as counter-rotating sets. A momentum theory based model was formulated that predicted counter-rotating performance using the propeller performance data. The counter-rotating data was used to determine the effectiveness of the method. <p> A solution was found that successfully predicted the counter-rotating performance of all of the tested propeller sets using six interaction coefficients. The optimal values of these coefficients were used to write two counter-rotating performance prediction programs. The first program takes the forward and aft RPMs and the flow speed as inputs, and predicts the generated thrust and torque. The second program takes the flow speed and the desired thrust as inputs and calculates the forward and aft RPM values that will generate the desired thrust while producing zero torque. The second program was used to determine the optimal counter-rotating set for the HSAUV.<br>Master of Science
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McCarthy, Martin. "Contra-rotating open rotor reverse thrust aerodynamics." Thesis, Cranfield University, 2011. http://dspace.lib.cranfield.ac.uk/handle/1826/10448.

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Reverse thrust operations of a model scale Contra-Rotating Open Rotor design were numerically modelled to produce individual rotor thrust and torque results comparable to experimental measurements. The aims of this research were to develop an understanding of the performance and aerodynamics of open rotors during thrust reversal operations and to establish whether numerical modelling with a CFD code can be used as a prediction tool given the highly complex flowfield. A methodology was developed from single rotor simulations initially before building a 3D‘frozen rotor’ steady-state approach to model contra-rotating blade rows in reverse thrust settings. Two different blade pitch combinations were investigated (β1,2 =+30°,- 10° and β1,2 =-10°,-20°). Thrust and torque results compared well to the experimental data and the effects of varying operating parameters, such as rpm and Mach number, were reproduced and in good agreement with the observed experimental behaviour. The main flow feature seen in all the reverse thrust cases modelled, both single rotor and CROR, is a large area of recirculation immediately downstream of the negative pitch rotor(s).This is a result of a large relative pressure drop region generated by the suction surfaces of the negative pitch blades. An initial 3D unsteady sliding-mesh calculation was performed for one CROR reverse thrust case. The thrust and torque values were in poor agreement with experimental values and the disadvantages relating to time costs and required computational resources for this technique were illustrated. However, the results did yield a nominal unsteady variation of thrust and torque due to rotor phase position. Overall the work shows that it may be possible to develop a CROR reverse thrust prediction tool of beneficial quality using CFD models. The research also shows that the frozen rotor approach can be adopted without undermining the fidelity of the results.
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Trlica, Karel. "Konstrukční návrh a měření tandemového čerpadla jako srdeční náhrady." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2018. http://www.nusl.cz/ntk/nusl-378490.

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This diploma thesis serves as a constructional study of an axial pump with a tandem arrangement of impellers. It may also be perceived as proposal of possible constructional variants that could be used as cardiac replacements. The thesis offers several conceptual variants, while the selected ones are elaborated in detail. Drawing documentation and 3D models are included in the attachment. The components were dimensioned according to the parameters necessary for proper heart function.
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Books on the topic "Counter Rotating Propeller"

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V, Sundt C., McKibbon A. H, and United States. National Aeronautics and Space Administration., eds. Advanced gearbox technology: Advanced counter-rotating gearbox : detailed design report. National Aeronautics and Space Administration, 1988.

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2

Center, Langley Research, ed. Annoyance caused by advanced turboprop aircraft flyover noise: Counter-rotating propeller configuration. National Aeronautics and Space Administration, 1990.

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A, Mulac Richard, Adamczyk John J, and Lewis Research Center, eds. A numerical simulation of the inviscid flow through a counter-rotating propeller. National Aeronautics and Space Administration, Lewis Research Center, 1986.

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4

C, Brown P., and United States. National Aeronautics and Space Administration., eds. Effect of angular inflow on the vibratory response of a counter-rotating propeller: By J.E. Turnberg, P.C. Brown. NASA, 1985.

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Center, Langley Research, ed. Advanced turboprop aircraft flyover noise: Annoyance to counter-rotating-propeller configurations with a different number of blades on each rotor : preliminary results. National Aeronautics and Space Administration, Langley Research Center, 1988.

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Center, Langley Research, ed. Advanced turboprop aircraft flyover noise: Annoyance to counter-rotating-propeller configurations with an equal number of blades on each rotor : preliminary results. National Aeronautics and Space Administration, Langley Research Center, 1988.

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C, Brown P., and United States. National Aeronautics and Space Administration, eds. Effect of angular inflow on the vibratory response of a counter-rotating propeller: By J.E. Turnberg, P.C. Brown. NASA, 1985.

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Dunham, Dana Morris. Low-speed wind-tunnel tests of single- and counter-rotation propellers. National Aeronautics and Space Administration Scientific and Technical Information Branch, 1986.

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Dunham, Dana Morris. Low-speed wind-tunnel tests of single- and counter-rotation propellers. Langley Research Center, 1986.

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L, Gentry Garl, Coe Paul L, and Langley Research Center, eds. Low-speed wind-tunnel tests of single- and counter-rotation propellers. National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.

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Book chapters on the topic "Counter Rotating Propeller"

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Kai, Wei, Cao Qi, Yan Qun, Xu Jian, and Xue Dongwen. "Experimental Study on Aeroacoustic of Counter-Rotating Propeller in Ground Acoustic Environment." In Computational and Experimental Simulations in Engineering. Springer International Publishing, 2023. http://dx.doi.org/10.1007/978-3-031-42987-3_69.

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Conference papers on the topic "Counter Rotating Propeller"

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Giovanetti, Eli, and Kenneth Hall. "Optimal Design of Compound Helicopters Using Higher Harmonic Control." In Vertical Flight Society 70th Annual Forum & Technology Display. The Vertical Flight Society, 2014. http://dx.doi.org/10.4050/f-0070-2014-9553.

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We investigate the optimal design of a compound helicopter comprised of counter-rotating coaxial rotors, a propeller, and optionally a fixed wing. We determine the blade geometry, azimuthal blade pitch inputs, optimal shaft angle (rotor angle of attack), and division of propulsive and lifting forces among the components that minimize the total power for a given flight condition. The optimal design problem is cast as a variational statement that minimizes the sum of induced and viscous power losses for a prescribed lift, propulsive force, and vehicle trim condition. The rotor, propeller, and wing geometry and control inputs are related to the far-field circulation through a lifting line model that accounts for experimentally or computationally determined nonlinear lift and drag polars. The variational statement is discretized using a vortex lattice wake, and the resulting nonlinear constrained optimization problem is solved via Newton iteration. We show that varying the prescribed propulsive force of the system affects the optimal shaft angle and rotor design, and that higher harmonic control reduces total vehicle power loss (inefficiency) in high speed flight by as much as 15 percent. We also show that imposing a maximum allowable lateral lift offset can greatly increase the power loss of the coaxial rotors.
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Angelov, Plamen, Maya Rankova, and Borislav Vuchkov. "MODERN METHODS OF DETERMINING OF THE MOMENTS WATER QUALITY. COMPARING THE RESULTS WITH TRADITIONAL METHOD." In 24th SGEM International Multidisciplinary Scientific GeoConference 2024. STEF92 Technology, 2024. https://doi.org/10.5593/sgem2024/3.1/s12.19.

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Hydrometric propeller methods, is device that responds and measuring the velocity of the water current at the point where its sensor axis is located. Mechanical hydrometric propellers are widely used in our country, in which the current causes rotation of a screw vane with an angular velocity proportional to the velocity of the current, in this method the depth of the river profile must be taken into account in order to comply with the measurement condition in 1, 2, or 3 points namely 0.2h, 0.6h and 0.8h, h-depth of flow [2] . In the present topic, a comparison will be made between a hydrometric propeller, a device for measuring speeds and depths based on the principle of magnetic induction. Graphs, tables and conclusions from field measurements will be presented. The device will be compared measures water velocity by using Faraday's principle of magnetic induction. This allows measurement of low velocities without rotating parts. The research will help solve problems during operational work (field work), will aim to show fast, accurate results in determining water quantities, shortening measurement time, using the device at low water levels, at small flows.
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DAVENPORT, F., J. COLEHOUR, and J. SOKHEY. "Analysis of counter-rotating propeller performance." In 23rd Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics, 1985. http://dx.doi.org/10.2514/6.1985-5.

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Olausson, Martin, Richard Avella´n, Niklas So¨rman, Filip Rudebeck, and Lars-Erik Eriksson. "Aeroacoustics and Performance Modeling of a Counter-Rotating Propfan." In ASME Turbo Expo 2010: Power for Land, Sea, and Air. ASMEDC, 2010. http://dx.doi.org/10.1115/gt2010-22543.

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This paper presents a method for design and analysis of counter-rotating propfans with respect to performance and aeroacoustics. The preliminary design method generates the ideal optimum propeller design corrected for losses in terms of profile and compressibility drag. The propeller design is further analyzed by computational fluid dynamics, CFD, to calculate the performance and the deterministic interaction noise. The unsteady flow around the propellers is calculated using URANS such that only one blade per propeller needs to be discretized. The unsteady pressure distribution around the blades is integrated, using a Ffowcs Williams-Hawkings method, to an observer for noise evaluation. The results of the performance analysis, the CFD computations and the aeroacoustic analysis are compared with experimental data available from the nonproprietary reports regarding the counter-rotating propellers developed in the 1980s.
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SHIVASHANKARA, B., D. JOHNSON, and R. CUTHBERTSON. "Installation effects on counter rotating propeller noise." In 13th Aeroacoustics Conference. American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-4023.

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Lesieutre, Daniel J., and John P. Sullivan. "The Analysis of Counter-Rotating Propeller Systems." In General Aviation Aircraft Meeting and Exposition. SAE International, 1985. http://dx.doi.org/10.4271/850869.

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LESIEUTRE, D., and J. SULLIVAN. "Unsteady forces on counter-rotating propeller blades." In 4th Applied Aerodynamics Conference. American Institute of Aeronautics and Astronautics, 1986. http://dx.doi.org/10.2514/6.1986-1804.

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BLOCK, P., R. KLATTE, and P. DRUEZ. "Counter-rotating propeller noise directivity and trends." In 10th Aeroacoustics Conference. American Institute of Aeronautics and Astronautics, 1986. http://dx.doi.org/10.2514/6.1986-1927.

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CHUNG, JIN-DEOG, JOSEPH HOUGH, and ROBERT NAGEL. "Interaction between rotors of a counter rotating propeller." In 13th Aeroacoustics Conference. American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-3976.

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PARZYCH, DAVID, and COLMAN SHATTUCK. "NOISE OF THE FAIREY GANNET COUNTER ROTATING PROPELLER." In 10th Aeroacoustics Conference. American Institute of Aeronautics and Astronautics, 1986. http://dx.doi.org/10.2514/6.1986-1895.

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