Relevant bibliographies by topics / Yawing moment

Academic literature on the topic 'Yawing moment'

Author: Grafiati
Published: 10 December 2022
Last updated: 28 January 2023

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Journal articles on the topic "Yawing moment"

1

Mohamad, Firdaus, Wisnoe Wirachman, Wahyu Kuntjoro, and Rizal E. M. Nasir. "The Effects of Split Drag Flaps on Directional Motion of UiTM’s BWB UAV Baseline-II E-4: Investigation Based on CFD Approach." Advanced Materials Research 433-440 (January 2012): 584–88. http://dx.doi.org/10.4028/www.scientific.net/amr.433-440.584.

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This paper presents a study about split drag flaps as control surfaces to generate yawing motion of a blended wing body aircraft. These flaps are attached on UiTM’s Blended Wing Body (BWB) Unmanned Aerial Vehicle (UAV) Baseline-II E-4. Deflection of split drag flaps on one side of the wing will produce asymmetric drag force and, as consequences, yawing moment will be produced. The yawing moment produced will rotate the nose of the BWB toward the wing with deflected split drag flaps. The study has been carried out using Computational Fluid Dynamics to obtain aerodynamics data with respect to various sideslip angles (ß). The simulation is running at 0.1 Mach number or about 35 m/s. Results in terms of dimensionless coefficient such as drag coefficient (CD), side force coefficient (CS) and yawing moment coefficient (Cn) are used to observe the effects of split drag Subscript text flaps on the yawing moment. All the results obtained shows linear trends for all curves with respect to sideslip angles (ß).
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Mohamad, Firdaus, Wirachman Wisnoe, Rizal E. M. Nasir, Khairul Imran Sainan, and Norhisyam Jenal. "Yaw Stability Analysis for UiTM's BWB Baseline-II UAV E-4." Applied Mechanics and Materials 393 (September 2013): 323–28. http://dx.doi.org/10.4028/www.scientific.net/amm.393.323.

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This paper presents a study about yaw stability analysis for UiTMs Blended-Wing-Body (BWB) Baseline-II E-4. This aircraft is equipped with split drag flaps in order to perform directional motion. One of the split drag flaps will be deflected to generate yawing moment. This yawing moment is generated through the drag that is produced upon deflection of flaps. The study was carried out using Computational Fluid Dynamics (CFD) for various sideslip angles (β) and various flaps deflection angle (δT). The simulation was conducted at 0.1 Mach number (35 m/s) and results in terms of coefficient such yawing and rolling moment are tabulated in order to determine the stability of the aircraft. The result reveals that the aircraft is directionally unstable. This is as expected because the aircraft does not have any vertical tail configuration to provide the yawing moment. However, high deflection of split flaps can still generate adequate restoring moment for the aircraft.
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Bartl, Jan, Franz Mühle, and Lars Sætran. "Wind tunnel study on power output and yaw moments for two yaw-controlled model wind turbines." Wind Energy Science 3, no. 2 (August 15, 2018): 489–502. http://dx.doi.org/10.5194/wes-3-489-2018.

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Abstract. In this experimental wind tunnel study the effects of intentional yaw misalignment on the power production and loads of a downstream turbine are investigated for full and partial wake overlap. Power, thrust force and yaw moment are measured on both the upstream and downstream turbine. The influence of inflow turbulence level and streamwise turbine separation distance are analyzed for full wake overlap. For partial wake overlap the concept of downstream turbine yawing for yaw moment mitigation is examined for different lateral offset positions. Results indicate that upstream turbine yaw misalignment is able to increase the combined power production of the two turbines for both partial and full wake overlap. For aligned turbine setups the combined power is increased between 3.5 % and 11 % depending on the inflow turbulence level and turbine separation distance. The increase in combined power is at the expense of increased yaw moments on both the upstream and downstream turbine. For partial wake overlap, yaw moments on the downstream turbine can be mitigated through upstream turbine yawing. Simultaneously, the combined power output of the turbine array is increased. A final test case demonstrates benefits for power and loads through downstream turbine yawing in partial wake overlap. Yaw moments can be decreased and the power increased by intentionally yawing the downstream turbine in the opposite direction.
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Park, Ji-Min, Dong-Hyun Kim, and Hyung-Ju Park. "Prediction of Yawing Moment for a Hand-Launched UAV Considering Interference Effect of Propeller Wake." Journal of the Korea Institute of Military Science and Technology 24, no. 4 (August 5, 2021): 426–34. http://dx.doi.org/10.9766/kimst.2021.24.4.426.

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In this paper, three-dimensional unsteady computational fluid dynamic(CFD) analyses based on overset grid technique have been performed for a hand-launched unmanned aerial vehicle(UAV) considering the wake effect generated by a rotating propeller. In addition, the defection of rudder is considered in order to consider to predict the equilibrium condition of yawing moment during cruise flight conditions. It is importantly shown in this paper that the wake interference effect of the propeller is significant to accurately predict the yawing moment of the UAV and the yawing moment coefficient corresponding to a flight speed can be different because of its different amount of wake effect due to the different rotating speed of the propeller.
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Ghadimi, Parviz, and Saeid Panahi. "Numerical investigation of hydrodynamic forces acting on the non-stepped and double-stepped planing hulls during yawed steady motion." Proceedings of the Institution of Mechanical Engineers, Part M: Journal of Engineering for the Maritime Environment 233, no. 2 (January 19, 2018): 428–42. http://dx.doi.org/10.1177/1475090217751549.

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This article focuses on the steady motion of yawed planing hulls with emphasis on the effects of adding steps to the bottom of these vessels on the hydrodynamic forces and moments acting on the boat. To analyze the problem, the Ansys-CFX software is used and three different planing hulls are investigated in steady yawed condition. The main targeted results include hydrodynamic forces and moments acting on the boat at different yaw angles and beam Froude numbers which provide important insights regarding the effects of loading and adding step on these forces and moments. The numerically predicted sway forces are compared against experimental data, suggesting that the current numerical model predicts sway and surge forces with reasonable accuracy. Moreover, it is observed that surge force coefficient of the investigated prismatic planing hull with light loading condition does not change significantly when the hull is relocated in a yaw angle, while it is remarkably affected when the boat is heavy. Furthermore, it is observed that this prismatic planing hull has smaller rolling moment in a steady yawed motion, when it moves at larger beam Froude number. Meanwhile, the computed yawing moments of this hull indicate that an increase in speed does not change this moment notably, while an increase in its weight yields larger yawing moment. Comparison of the results of stepped and non-stepped planing hulls indicates that surge force coefficient of the stepped hull is larger, while its sway force and rolling moment are smaller. This is mainly caused by the shape of the interrupted wetted surface and larger number of maximum pressure area in the stepped planing hull. Finally, it is concluded that there is no significant difference between the yawing moment of the investigated stepped and non-stepped planing hulls.
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Hu, Xing Jun, Peng Qin, Peng Guo, and Jing Yu Wang. "Influence of Front Shape on Crosswind Aerodynamic Loads of Heavy-Duty Truck: A Numerical Case Study." Advanced Materials Research 569 (September 2012): 428–32. http://dx.doi.org/10.4028/www.scientific.net/amr.569.428.

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Research was done on the crosswind aerodynamic loads of three different front shape heavy-duty trucks by the method of numerical simulation. According to the research, the side force and the rolling moment of truck change slightly, but the drag and yawing moment changes dramatically when running in strong crosswind with different front shapes. The conclusions were drawn from discussion that the long head heavy-duty truck has the least yawing moment among the studied trucks so it has the best driving stability correspondingly.
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7

Shearwood, Thomas R., Mostafa R. A. Nabawy, William J. Crowther, and Clyde Warsop. "A Novel Control Allocation Method for Yaw Control of Tailless Aircraft." Aerospace 7, no. 10 (October 19, 2020): 150. http://dx.doi.org/10.3390/aerospace7100150.

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Tailless aircraft without vertical stabilisers typically use drag effectors in the form of spoilers or split flaps to generate control moments in yaw. This paper introduces a novel control allocation method by which full three-axis control authority can be achieved by the use of conventional lift effectors only, which reduces system complexity and control deflection required to achieve a given yawing moment. The proposed method is based on synthesis of control allocation modes that generate asymmetric profile and lift induced drag whilst maintaining the lift, pitching moment and rolling moment at the trim state. The method uses low order models for aerodynamic behaviour characterisation based on thin aerofoil theory, lifting surface methodology and ESDU datasheets and is applied to trapezoidal wings of varying sweep and taper. Control allocation modes are derived using the zero-sets of surrogate models for the characterised aerodynamic behaviours. Results are presented in the form of control allocations for a range of trimmed sideslip angles up to 10 degrees optimised for either maximum aerodynamic efficiency (minimum drag for a specific yawing moment) or minimum aggregate control deflection (as a surrogate observability metric). Outcomes for the two optimisation objectives are correlated in that minimum deflection solutions are always consistent with efficient ones. A configuration with conventional drag effector is used as a reference baseline. It is shown that, through appropriate allocation of lift based control effectors, a given yawing moment can be produced with up to a factor of eight less aggregate control deflection and up to 30% less overall drag compared to use of a conventional drag effector.
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Brincklow, J. R., and D. F. Hunsaker. "Aileron size and location to minimise induced drag during rolling-moment production at zero rolling rate." Aeronautical Journal 125, no. 1287 (April 12, 2021): 807–29. http://dx.doi.org/10.1017/aer.2020.139.

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AbstractMost modern aircraft employ discrete ailerons for roll control. The induced drag, rolling moment, and yawing moment for an aircraft depend in part on the location and size of the ailerons. In the present study, lifting-line theory is used to formulate theoretical relationships between aileron design and the resulting forces and moments. The theory predicts that the optimum aileron geometry is independent of prescribed lift and rolling moment. A numerical potential flow algorithm is used to evaluate the optimum size and location of ailerons for a wide range of planforms with varying aspect ratio and taper ratio. Results show that the optimum aileron design to minimise induced drag always extends to the wing tip. Impacts to induced drag and yawing moment are also considered, and results can be used to inform initial design and placement of ailerons on future aircraft. Results of this optimisation study are also compared to theoretical optimum results that could be obtained from morphing-wing technology. Results of this comparison can be used to evaluate the potential benefits of using morphing-wing technology rather than traditional discrete ailerons.
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9

Malik, Bilal, Suhail Akhtar, and Jehanzeb Masud. "Aircraft spin characteristics with high-alpha yawing moment asymmetry." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 15 (July 12, 2017): 2793–806. http://dx.doi.org/10.1177/0954410017718215.

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This paper analyzes the open-loop spin dynamics of a fighter configuration that exhibits yawing moment asymmetry at high angles of attack. High-fidelity aerodynamic model, in a look-up-tables form, is developed using the experimental data from static, coning, and oscillatory coning rotary balance wind tunnel tests. As a first step, all attainable equilibrium spin modes along with their sensitivity to control settings are predicted. Investigation of the dynamic characteristics of the predicted spin modes is performed using six degrees-of-freedom time history simulations, which showed that both, right and left flat spins are oscillatory and divergent. Influence of high-alpha yawing moment asymmetry on the spin recovery piloting strategies with control inputs is also studied with six degrees-of-freedom time history simulations. Our studies reveal that the proposed spin recovery strategies effectively reduce the recovery time for the left flat spins. However, aircraft’s inherent tendency to yaw rightwards due to high-alpha yawing moment asymmetry renders proposed spin recovery strategies ineffective in accelerating the recovery of the right flat spins.
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Sachs, Gottfried. "Aerodynamic yawing moment characteristics of bird wings." Journal of Theoretical Biology 234, no. 4 (June 2005): 471–78. http://dx.doi.org/10.1016/j.jtbi.2004.12.001.

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Books on the topic "Yawing moment"

1

Cobleigh, Brent R. Comparison of X-31 flight and ground-based yawing moment asymmetries at high angles of attack. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 2001.

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2

Messina, Michael D. Using the HARV simulation aerodynamic model to determine forebody strake aerodynamic coefficients from flight data. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

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3

A, Croom Mark, and Dryden Flight Research Facility, eds. Comparison of X-31 flight and ground-based yawing moment asymmetries at high angles of attack. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 2001.

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A, Croom Mark, and Dryden Flight Research Facility, eds. Comparison of X-31 flight and ground-based yawing moment asymmetries at high angles of attack. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 2001.

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A, Croom Mark, and Dryden Flight Research Facility, eds. Comparison of X-31 flight and ground-based yawing moment asymmetries at high angles of attack. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 2001.

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6

United States. National Aeronautics and Space Administration., ed. Differential canard deflection for generation of yawing moment on the X-31 with and without the vertical tail. [Washington, DC: National Aeronautics and Space Administration, 1996.

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United States. National Aeronautics and Space Administration., ed. Differential canard deflection for generation of yawing moment on the X-31 with and without the vertical tail. [Washington, DC: National Aeronautics and Space Administration, 1996.

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8

United States. National Aeronautics and Space Administration., ed. Sailplane glide performance and control using fixed and articulating winglets: A thesis. [Washington, DC: National Aeronautics and Space Administration, 1995.

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Center, Ames Research, ed. Numerical analysis of tangential slot blowing on a generic chined forebody. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1994.

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J, O'Rourke Matthew, and Langley Research Center, eds. Exploratory investigation of forebody strakes for yaw control of a generic fighter with a symmetric 60⁰ half-angle chine forebody. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

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Book chapters on the topic "Yawing moment"

1

Ben-Ami, Shlomo. "Oh Jerusalem! (and Its Lies)." In Prophets without Honor, 76–82. Oxford University Press, 2022. http://dx.doi.org/10.1093/oso/9780190060473.003.0012.

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The backchannel, Barak preferred to belittle it as “the intellectual exercise” and called for collective team reflection on our capacity to make further progress on Jerusalem. We all departed from our comfort zone on Jerusalem, not enough though to meet Arafat’s resilient requirements. Barak liked such brainstorming sessions, which he could sum up with inspiring rhetoric, but alas, he was always hesitant to translate it into concrete policy moves. Such moves were necessary now not just because we were in the defining moments of a peace summit, but also because of the yawning gap that existed between the Jerusalem of our imagination and the real one. While we were still hesitantly considering ceding functions and rights to the Palestinians in the Holy City, Jerusalem was already, for all practical purposes, a divided city.
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Conference papers on the topic "Yawing moment"

1

Amano, Ryoichi S., Yi-Hsin Yen, and Bryan Sinkovec. "Analysis of Lift Force, Drag Force, Side Force, Pitching Moment, Yawing Moment, and Rolling Moment." In 53rd AIAA Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-1888.

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Matsui, Akitoshi, and Koichi Hishida. "Effective Body Shape for Reducing Yawing Moment in Cross Wind." In ASME-JSME-KSME 2011 Joint Fluids Engineering Conference. ASMEDC, 2011. http://dx.doi.org/10.1115/ajk2011-23024.

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Reductions of the side force and the connected yawing moment are of significance for driving stability under cross wind. This paper shows the suitable body shape under unsteady cross wind for reducing side force and yawing moment. Numerically, the shape changes such as rounded and/or cut off corners and patterned indented side surface under steady cross wind are evaluated, using k-ε model. The adequate shapes from the numerical data are experimentally validated under steady and unsteady cross wind in a wind tunnel. Flow structure and, side force and yawing moment are examined by High-speed PIV and a three-component load cell, respectively.
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Hunsaker, Douglas F., Bruno Moorthamers, and James J. Joo. "Minimum-Frequency Spanwise Twist for Yawing-Moment Control During Roll." In AIAA Aviation 2019 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2019. http://dx.doi.org/10.2514/6.2019-2917.

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4

Wang, Yucheng. "The Side Force and Yawing Moment in Archaeological Boating Sailing." In 2016 International Conference on Mechatronics Engineering and Information Technology. Paris, France: Atlantis Press, 2016. http://dx.doi.org/10.2991/icmeit-16.2016.12.

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Qin, Ye, Yankui Wang, and Qian Li. "Investigation on Non-linear Characteristic of Yawing Moment of Twin-tailed Configuration." In 32nd AIAA Applied Aerodynamics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2014. http://dx.doi.org/10.2514/6.2014-2992.

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Sohail, Muhammad Amjad, Zaka Muhammad, Mukkarum Husain, Muhammad Yamin Younis, Jiachun Li, and Song Fu. "Effects of Mach Numbers on Side Force, Yawing Moment and Surface Pressure." In RECENT PROGRESSES IN FLUID DYNAMICS RESEARCH: Proceeding of the Sixth International Conference on Fluid Mechanics. AIP, 2011. http://dx.doi.org/10.1063/1.3651865.

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Hao, Zhanzhou, Bo Yin, Guowei Yang, and Pan Xiao. "Effect of Aerodynamic Moment on High-Speed Maglev Train Under Complicated Conditions." In ASME 2021 Fluids Engineering Division Summer Meeting. American Society of Mechanical Engineers, 2021. http://dx.doi.org/10.1115/fedsm2021-61883.

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Abstract As the next generation of high-speed rail transportation, the high-speed maglev train has a design speed of 600km/h, whose Mach number is about 0.49. The severe aerodynamic effect caused by this high speed has a substantial impact on the train’s stability and safety. In this paper, the aerodynamic moments of two three-carriage maglev trains passing by each other in open air are investigated by numerical simulation. To get transient moments acting on the train, this study adopted the sliding mesh method and the k-ε turbulent model, and a user-defined function was compiled to define the motion of maglev. The results show that the pitching moment is the most important factor for the steady of maglev trains running in the open air. The oscillation of the total aerodynamic moment mainly comes from the moment acting on the lower part. The coupling of the pitching moment acting on the upper and lower part of carriages make the peak of the total pitching moment behind the total yawing moment.
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Zhuang, Jiayuan, Jian Cao, Yumin Su, Lei Zhang, and Xianzhao Yu. "Experimental Study on Hydrodynamic Performance of Mini-AUV in Non-Uniform Flow Field." In ASME 2019 38th International Conference on Ocean, Offshore and Arctic Engineering. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/omae2019-96835.

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Abstract Experimental investigations of hydrodynamic performance of mini-AUV in non-uniform flow field were conducted in the basin of Harbin Engineering University, the revolved body and flat body of mini-AUV model were tested respectively. The three dimensional flow fields were generated by local jet of the underwater pump, and circulated in the basin. The three dimensional velocity distributions at different positions were measured by a Doppler current profiler. The three component balance was used to measure the drag, lateral force and yawing moment acting on the mini-AUV models depending on drift angle in the flow field, and the influence of complex flow field to the hydrodynamic performance of mini-AUV indicated that drag was not sensitive to drift angle and yawing moment was increased obviously. The conducted experiments could supply reference to the maneuverability research of mini-AUV in real marine environments in the future.
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Fernandes, Antonio Carlos, and Mohammadmehdi Armandei. "Extracting Energy From the Hydrodynamic Instability of a Yawing Flat Plate." In ASME 2012 31st International Conference on Ocean, Offshore and Arctic Engineering. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/omae2012-84165.

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The extraction of energy from currents is still an issue. Both design point and off-design behavior should be addressed conveniently. In the present study, a new concept based on the flow-induced instability of an elastic structure is introduced by which the energy can be extracted from the water current. The energy extractor device is named “Fernandes-Armandei”, which consists of a simple flat plate attached to a torsion spring and located vertically in the water current. The flat plate has only 1 DOF that is yawing about its axis, which is in its mid chord length. A concurrent-schedule research (Armandei and Fernandes, 2012) demonstrates that one such motion becomes dynamically unstable, as the velocity exceeds a special threshold. The motivation of doing this research was the robustness of the oscillations created due to the flow-induced instability. Two different cases (a) and (b) are studied, case (a) with larger natural frequency and case (b) with larger mass moment and added moment of inertia. A damper is also applied in the device as a transmission system which converts oscillation to rotation. The rotary motion is utilized to lift a weight up to a prescribed height, to assess the energy extraction behavior of each case. The results show that case (b) can lift heavier weights than case (a). However, the maximum efficiency of case (a) (9.18%) is about three times more than the maximum efficiency of case (b) (3.26%).
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10

Cobleigh, Brent. "High-angle-of-attack yawing moment asymmetry of the X-31 aircraft from flight test." In 12th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1994. http://dx.doi.org/10.2514/6.1994-1803.

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