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Artykuły w czasopismach na temat „Blended-wing-body aircraft”

Autor: Grafiati

Data publikacji: 4 czerwca 2021

Data aktualizacji: 19 lutego 2022

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1

Qin, N., A. Vavalle, A. Le Moigne, M. Laban, K. Hackett i P. Weinerfelt. "Aerodynamic considerations of blended wing body aircraft". Progress in Aerospace Sciences 40, nr 6 (sierpień 2004): 321–43. http://dx.doi.org/10.1016/j.paerosci.2004.08.001.

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Qin, Ning, Armando Vavalle i Alan Le Moigne. "Spanwise Lift Distribution for Blended Wing Body Aircraft." Journal of Aircraft 42, nr 2 (marzec 2005): 356–65. http://dx.doi.org/10.2514/1.4229.

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Zhu, Wensheng, Xiongqing Yu i Yu Wang. "Layout Optimization for Blended Wing Body Aircraft Structure". International Journal of Aeronautical and Space Sciences 20, nr 4 (16.05.2019): 879–90. http://dx.doi.org/10.1007/s42405-019-00172-7.

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Dimopoulos, Thomas, Pericles Panagiotou i Kyros Yakinthos. "Stability study and flight simulation of a blended-wing-body UAV". MATEC Web of Conferences 304 (2019): 02013. http://dx.doi.org/10.1051/matecconf/201930402013.

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This article is a product of the design process of a Blended-Wing- Body Unmanned Aerial Vehicle (BWB UAV). The BWB geometry blends the wing and the fuselage so that the fuselage also contributes in lift generation. This geometry reduces the lift to drag ratio significantly, however it also compromises the aircraft’s stability and controllability, since there is no horizontal and vertical tail. As these features are absent from the BWB layout, the need to incorporate their functions in the new geometry arises so that they cover stability demands sufficiently, according to aircraft of similar size, use and speed. Additionally, the method used for stability studies of conventional aircraft must also be adapted. This article covers the adaptation of the method to the new BWB geometry, its results in comparison to those of conventional aircraft and the use of the results for a computational simulation of the aircraft’ flight.

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5

Velicki, A., i P. Thrash. "Blended wing body structural concept development". Aeronautical Journal 114, nr 1158 (sierpień 2010): 513–19. http://dx.doi.org/10.1017/s0001924000004000.

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Abstract A lightweight robust airframe design is one of the key technological advancements necessary for the successful launch of a blended wing body aircraft. The non-circular pressure cabin dictates that substantial improvements beyond current state-of-the-art aluminium and composite structures is needed, and that improvements of this magnitude will require radically new airframe design and manufacturing practices. Such an approach is described in this paper. It is a highly integrated structural concept that is tailored and optimised to fully exploit the orthotropic nature and unique processing advantages inherent in dry carbon fibres, while also employing stitching to enable a unique damage-arrest design approach.

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6

Xu, Xin, Qiang Li, Dawei Liu, Keming Cheng i Dehua Chen. "Geometric Effects Analysis and Verification of V-Shaped Support Interference on Blended Wing Body Aircraft". Applied Sciences 10, nr 5 (28.02.2020): 1596. http://dx.doi.org/10.3390/app10051596.

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A special V-shaped support for blended wing body aircraft was designed and applied in high-speed wind tunnel tests. In order to reduce the support interference and explore the design criteria of the V-shaped support, interference characteristics and geometric parameter effects of V-shaped support on blended wing body aircraft were numerically studied. According to the numerical results, the corresponding dummy V-shaped supports were designed and manufactured, and verification tests was conducted in a 2.4 m × 2.4 m transonic wind tunnel. The test results were in good agreement with the numerical simulation. Results indicated that pitching moment of blended wing body aircraft is quite sensitive to the V-shaped support geometric parameters, and the influence of the inflection angle is the most serious. To minimize the pitching moment interference, the straight-section diameter and inflection angle should be increased while the straight-section length should be shortened. The results could be used to design special V-shaped support for blended wing body aircraft in wind tunnel tests, reduce support interference, and improve the accuracy of test results.

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7

Romli, Fairuz Izzuddin, i Mohd Syahidie Kamaruddin. "Emissions Performance Study for Conventional Aircraft Designs". Applied Mechanics and Materials 225 (listopad 2012): 385–90. http://dx.doi.org/10.4028/www.scientific.net/amm.225.385.

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Conventional aircraft designs have been highly successful within commercial passengers transport markets for a very long time, as evident from current fleet of many airlines. However, with the anticipated stricter environmental regulations to be imposed on future flight operations by the related governing bodies, the relevance of conventional aircraft designs to remain competitive has been questioned. On the other hand, some research ventures have been made to pursue revolutionary designs like blended wing body (BWB). This study aims to preliminarily assess the comparison of expected future emission performance between conventional aircraft design and blended wing body design. It addresses the ongoing debate on whether conventional aircraft designs can be expected to be able to cope with impending stricter environmental regulations and/or whether the venture into revolutionary designs is really necessary. Analyses done are largely based on the historical trends of conventional aircraft designs with regards to the lift-to-drag ratio and fuel consumption parameters. As for the blended wing body, its projected emissions performance is based on published data in the literature. The outcome from these analyses solidifies the belief that conventional aircraft designs will face tougher chances to remain operational under new environmental regulations and the search for revolutionary design with better aerodynamic efficiency such as blended wing body is becoming rather necessary.

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8

van Dommelen, Jorrit, i Roelof Vos. "Conceptual design and analysis of blended-wing-body aircraft". Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 228, nr 13 (29.01.2014): 2452–74. http://dx.doi.org/10.1177/0954410013518696.

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Due to the unconventional nature of the blended wing body (BWB) no off-the-shelf software package exists for its conceptual design. This study details a first step towards the implementation of traditional and BWB-specific design and analysis methods into a software tool to enable preliminary sizing of a BWB. The tool is able to generate and analyze different BWB configurations on a conceptual level. This paper investigates three different BWB configurations. The first configuration is an aft-swept BWB with aft-mounted engines, the second configuration is an aft-swept BWB with wing-mounted engines and the third configuration is a forward-swept BWB with wing-mounted engines. These aircraft comply with the same set of top-level requirements and airworthiness requirements. Each of the designs has been optimized for maximum harmonic range, while keeping its maximum take-off weight constant and identical. Results show that the forward-swept configuration with wing-mounted engines has the highest harmonic range. These findings warrant further investigation in this configuration and other alternative BWB configurations.

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9

Hong, Wei Jiang, i Dong Li Ma. "Influence of Control Coupling Effect on Landing Performance of Flying Wing Aircraft". Applied Mechanics and Materials 829 (marzec 2016): 110–17. http://dx.doi.org/10.4028/www.scientific.net/amm.829.110.

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As flying wing aircraft has no tail and adopts blended-wing-body design, most of flying wing aircrafts are directional unstable. Pitching moment couples seriously with rolling and yawing moment when control surfaces are deflected, bringing insecurity to landing stage. Numerical simulation method and semi-empirical equation estimate method were combined to obtain a high aspect ratio flying wing aircraft’s aerodynamic coefficients. Modeling and simulation of landing stage were established by MATLAB/Simulink. The control coupling effect on lift and drag characteristics and anti-crosswind landing capability was studied. The calculation results show that when the high aspect ratio flying wing aircraft was falling into the deceleration phase, appropriate to increase the opening angle of split drag rudder can reduce the trimming pitching moment deflection of pitch flap, thereby reduce the loss of lift caused by the deflection of pitch flaps. Flying wing aircraft can be rounded out successfully by using the pitch flap gently and steady. Both side-slip method and crabbed method can be applied to the landing of high aspect ratio flying wing aircraft in crosswind, the flying wing aircraft’s anti-crosswind landing capability was weakened by the control coupling effect of split drag rudder and elevon. Sideslip method was recommended in the crosswind landing of flying wing aircraft after calculation and analysis.

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10

Mulyanto, Taufiq, i M. Luthfi Nurhakim. "CONCEPTUAL DESIGN OF BLENDED WING BODY BUSINESS JET AIRCRAFT". Journal of KONES. Powertrain and Transport 20, nr 4 (1.01.2015): 299–306. http://dx.doi.org/10.5604/12314005.1137630.

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11

Paudel, Sanjiv. "Aerodynamic and Stability Analysis of Blended Wing Body Aircraft". International Journal of Mechanical Engineering and Applications 4, nr 4 (2016): 143. http://dx.doi.org/10.11648/j.ijmea.20160404.12.

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12

Ruseno, Neno. "Modal Analysis Of Blended Wing-Body UAV". Jurnal Teknologi Kedirgantaraan 6, nr 2 (31.08.2021): 68–75. http://dx.doi.org/10.35894/jtk.v6i2.39.

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The modal analysis deals with the dynamic behavior of mechanical structures under the dynamic vibration. This study aims to analyze the vibration characteristic of the blended wing-body Unmanned Aerial Vehicle (UAV) using modal analysis. The numerical method is used to calculate the eigen frequencies of the system. The COMSOL Multiphysics is selected as the Finite Element Method (FEM) software to simulate the study. The resulted eigen frequencies are 278.05 Hz, 721.28 Hz, 816.39 Hz, 1601.7 Hz, 1699.5 Hz, and 1855.5 Hz. The study also evaluates the displacement of the leading edge of the wing in all axes to understand the modal shapes. The modal shapes found are updrift, swift back, flapping vertical, flapping horizontal, flapping opposite horizontal and flapping more wave in horizontal movement. The comparison of resulted eigen frequencies with a conventional aircraft wing is conducted to understand the difference in its vibration characteristics.

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13

Mat, Shabudin, I. Shah Ishak, Khidzir Zakaria i Z. Ajis Khan. "Manufacturing Process of Blended Delta-Shaped Wing Model". Advanced Materials Research 845 (grudzień 2013): 971–74. http://dx.doi.org/10.4028/www.scientific.net/amr.845.971.

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Aerodynamicists have long acknowledged the blended wing body (BWB) aircraft design could produce great aerodynamic advantages due to the integration of the delta wing structure with the thick center body. Therefore the wind tunnel test campaign is crucial to gain information of the flow field that governs the delta-shaped wing which has frequently baffled the aerodynamicists. In such, the wind tunnel test required acceptable quality of delta-shaped wing model for results validity. Consequently, the manufacturing process as well as the selection of the appropriate machinery tools, must be wisely designed and performed. The modular 3D concept in associating with CAD/CAM technology was utilised in the process. Finally, the actual flow cycle of manufactures blended BWB aircraft model was sucessfully established. The objective of this paper is to highlight those complexity manufacturing process and techniques involved in order to produce a good blended delta-shaped wind tunnel model.

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14

Yan, Wan Fang, Jiang Hao Wu i Yan Lai Zhang. "Aerodynamic Performance of Blended Wing Body Aircraft with Distributed Propulsion". Advanced Materials Research 1016 (sierpień 2014): 354–58. http://dx.doi.org/10.4028/www.scientific.net/amr.1016.354.

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A 350-passenger BWB with a distributed propulsion system configuration is carried out and its aerodynamic performance in cruising and taking off are analyzed and discussed. It is shown from computation that the integrated configuration has a commendable aerodynamic performance in cruising and taking off. The cruise lift to drag ratio is reach to 24.0 in cruising. The ingestion effect of the propulsion system leads to a high lift at a low speed. The maximum lift coefficient CLmax is 1.62 when α=20° in taking off. In addition, the ingestion also delays the flow separation on the upper surface of center body, which contributes to a well stall performance of the configuration at large angle of attack.

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15

Cai, Chen Fang, Jiang Hao Wu i Bin Liang. "The Effect of Gust on Blended-Wing-Body Civil Aircraft". Advanced Materials Research 1016 (sierpień 2014): 359–64. http://dx.doi.org/10.4028/www.scientific.net/amr.1016.359.

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In this paper, aerodynamic properties of Blended Wing Body (BWB) civil aircraft are studied by two models: one calls complete model that is computed by numerical simulation coupling equations of motion with the Navier-Stokes equations, and the other doesn’t consider the equations of motion (without dynamic response). The results show that the model without dynamic response can also correctly predict the trend of the dynamic properties compared with complete model. Nevertheless, there are some quantitative differences existing between the complete model and the model without dynamic response.

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16

Su, Weihua, i Carlos E. S. Cesnik. "Nonlinear Aeroelasticity of a Very Flexible Blended-Wing-Body Aircraft". Journal of Aircraft 47, nr 5 (wrzesień 2010): 1539–53. http://dx.doi.org/10.2514/1.47317.

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17

Okonkwo, Paul, i Howard Smith. "Review of evolving trends in blended wing body aircraft design". Progress in Aerospace Sciences 82 (kwiecień 2016): 1–23. http://dx.doi.org/10.1016/j.paerosci.2015.12.002.

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18

Lyu, Zhoujie, i Joaquim R. R. A. Martins. "Aerodynamic Design Optimization Studies of a Blended-Wing-Body Aircraft". Journal of Aircraft 51, nr 5 (wrzesień 2014): 1604–17. http://dx.doi.org/10.2514/1.c032491.

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19

Peigin, Sergey, i Boris Epstein. "Computational Fluid Dynamics Driven Optimization of Blended Wing Body Aircraft". AIAA Journal 44, nr 11 (listopad 2006): 2736–45. http://dx.doi.org/10.2514/1.19757.

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20

Gebbie, David A., Mark F. Reeder, Charles Tyler, Vladamir Fonov i Jim Crafton. "Lift and Drag Characteristics of a Blended-Wing Body Aircraft". Journal of Aircraft 44, nr 5 (wrzesień 2007): 1409–21. http://dx.doi.org/10.2514/1.22356.

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21

Jia, Yuan, Jinye Li i Jianghao Wu. "Power Fan Design of Blended-Wing-Body Aircraft with Distributed Propulsion System". International Journal of Aerospace Engineering 2021 (7.09.2021): 1–18. http://dx.doi.org/10.1155/2021/5128136.

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A blended-wing-body aircraft has the advantages of high lift-to-drag ratio, low noise, and high economy compared with traditional aircraft. It is currently a solution with great potential to become a future civilian passenger aircraft. However, most airplanes with this layout use distributed power, and the power system is on the back of the fuselage, with embedded or back-supported engines. This type of design causes the boundary layer suction effect. The boundary layer ingestion (BLI) effect can fill the wake of the aircraft and improve the propulsion efficiency of the engine. However, it causes huge design difficulties, especially when the aircraft and the engine are strongly coupled. In this paper, an aircraft with a coupled engine configuration is studied. The internal and external flow fields are calculated through numerical simulation. A realistic calculation model is obtained through the coupling of boundary conditions. On the basis of the influence of the external flow on the internal flow under the coupled condition, the influence of the BLI effect on the aerodynamic performance of the fan is investigated.

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22

van der Voet, Z., F. J. J. M. M. Geuskens, T. J. Ahmed, B. Ninaber van Eyben i A. Beukers. "Configuration of the Multibubble Pressure Cabin in Blended Wing Body Aircraft". Journal of Aircraft 49, nr 4 (lipiec 2012): 991–1007. http://dx.doi.org/10.2514/1.c031442.

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Claudia Alice, STATE. "A Linear Analysis of a Blended Wing Body (BWB)Aircraft Model". INCAS BULLETIN 3, nr 3 (16.09.2011): 115–26. http://dx.doi.org/10.13111/2066-8201.2011.3.3.12.

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Sturm, Ralf, i Martin Hepperle. "Crashworthiness and ditching behaviour of blended-wing-body (BWB) aircraft design". International Journal of Crashworthiness 20, nr 6 (4.08.2015): 592–601. http://dx.doi.org/10.1080/13588265.2015.1068997.

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25

KATSURAYAMA, Yohei, i Taro IMAMURA. "Numerical Simulation of Engine Noise Shielding around Blended Wing Body Aircraft". TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 58, nr 2 (2015): 83–88. http://dx.doi.org/10.2322/tjsass.58.83.

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26

ZHU, Wensheng, Zhouwei FAN i Xiongqing YU. "Structural mass prediction in conceptual design of blended-wing-body aircraft". Chinese Journal of Aeronautics 32, nr 11 (listopad 2019): 2455–65. http://dx.doi.org/10.1016/j.cja.2019.08.003.

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Larkin, Geoffrey, i Graham Coates. "A design analysis of vertical stabilisers for Blended Wing Body aircraft". Aerospace Science and Technology 64 (maj 2017): 237–52. http://dx.doi.org/10.1016/j.ast.2017.02.001.

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28

Zhang, Li, Zhenghong Gao i Yiming Du. "Study on Cruise Drag Characteristics of Low Drag Normal Layout Civil Aircraft". Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 38, nr 3 (czerwiec 2020): 580–88. http://dx.doi.org/10.1051/jnwpu/20203830580.

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This paper focus on the wing shape related drag reduction measures of normal layout civil aircraft, through the drag reduction to improve the aircraft performance. Mainly by the laminar flow wing to reduce skin drag and weak shock wave wing to reduce shock drag, to keep a section of laminar zone on the wing leading edge to reduce skin drag, the wing profile's pressure distribution transit from the middle part's tonsure pressure zone to the trailing edge's inverse pressure gradient zone gentle to reduce the shock drag. The wing body junction plus the body belly fairing to increase the junction flow velocity, through increase flow velocity to weak the boundary layer stacked at the junction, improve the drag performance. The blended winglet to reduce the wing tip induced drag, study the shape parameters impact on the drag reduction, longitudinal moment and directional moment, attain the winglet model with drag reduction effect, suitable pitching moment and directional moment. For the wing body fairing have significant impact on the wing shape lower surface pressure distribution, the winglet have important impact on the wing tip flow, so the single part drag reduction measure is not feasible, need to carry out integrated drag reduction study on the wing related three drag reduction measures, and study the drag reduction measure's drag reduction decrement, put a reference for the normal layout civil aircraft's drag reduction. Through the above drag reduction measure's assessment attain the effect of drag reduction and rising the normal layout civil aircraft's cruise ratio, improving the cruise performance.

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29

Xu, Xin, Dawei Liu, Keming Cheng i Dehua Chen. "Design and experimental validation of a specialized pressure-measuring rake for blended wing body aircraft’s unconventional inner flow channel". Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 234, nr 15 (6.07.2020): 2186–96. http://dx.doi.org/10.1177/0954410020938971.

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The internal drag of the unconventional inner flow channel of blended wing body aircraft must be measured accurately to correct the air intake effect of the blended wing body flow-through model in wind tunnel tests. In this study, the pressure distribution of the inner flow channel under the interaction of internal and external flows was obtained through numerical simulation. A specialized pressure-measuring rake was designed based on the numerical results, and a validation test was conducted in a 2.4 m × 2.4 m transonic wind tunnel. Compared with the flow in traditional inlets/nozzles, the flow in the unconventional inner channel in the current research is asymmetric, the distortion index is higher, and the internal drag is more sensitive to flow changes. The wind tunnel test results have a good correlation with the numerical results, and the repeatability of the test results is satisfactory, indicating that the measurement accuracy and precision of the pressure-measuring rake are acceptable. The design method of the specialized rake is feasible, and it can be used to guide the measurement of complex flow in unconventional inner flow channels of blended wing body aircraft.

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30

Cook, M. V., i H. V. de Castro. "The longitudinal flying qualities of a blended-wing-body civil transport aircraft". Aeronautical Journal 108, nr 1080 (luty 2004): 75–84. http://dx.doi.org/10.1017/s0001924000005029.

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Abstract This paper describes an evaluation of the longitudinal flying qualities of a generic blended-wing-body (BWB) transport aircraft at low speed flight conditions. Aerodynamic data was obtained from several sources and integrated into the equations of motion of a typical BWB configuration in order to provide a reasonable basis for flying qualities assessment. The control requirements to trim are enumerated for a representative range of cg position and static margin over the typical range of approach speeds for both stable and unstable configurations. The linear dynamic characteristics of the unaugmented airframe are also described for the same range of stability margin. Subsequent work describes the development of a rate command-attitude hold command and stability augmentation system configured to comply with representative modern handling criteria. Finally, the flight dynamics of the augmented aircraft are described after refinement of the control law by means of piloted simulation in a fixed base flight simulator.

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31

Westermayer, C., A. Schirrer, M. Hemedi i M. Kozek. "Linear parameter-varying control of a large blended wing body flexible aircraft". IFAC Proceedings Volumes 43, nr 15 (2010): 19–24. http://dx.doi.org/10.3182/20100906-5-jp-2022.00005.

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32

Rahman, Naveed U., i James F. Whidborne. "Propulsion and Flight Controls Integration for a Blended-Wing-Body Transport Aircraft". Journal of Aircraft 47, nr 3 (maj 2010): 895–903. http://dx.doi.org/10.2514/1.46195.

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Ahn, Jongmin, Kijoon Kim, Seungkeun Kim i Jinyoung Suk. "Reconfigurable Flight Control Design for the Complex Damaged Blended Wing Body Aircraft". International Journal of Aeronautical and Space Sciences 18, nr 2 (30.06.2017): 290–99. http://dx.doi.org/10.5139/ijass.2017.18.2.290.

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Leifsson, L., A. Ko, W. H. Mason, J. A. Schetz, B. Grossman i R. T. Haftka. "Multidisciplinary design optimization of blended-wing-body transport aircraft with distributed propulsion". Aerospace Science and Technology 25, nr 1 (marzec 2013): 16–28. http://dx.doi.org/10.1016/j.ast.2011.12.004.

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35

Moigne, A. Le, i N. Qin. "Aerofoil profile and sweep optimisation for a blended wing-body aircraft using a discrete adjoint method". Aeronautical Journal 110, nr 1111 (wrzesień 2006): 589–604. http://dx.doi.org/10.1017/s0001924000001457.

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Abstract Aerodynamic optimisations of a blended wing-body (BWB) aircraft are presented. A discrete adjoint solver is used to calculate efficiently the gradients, which makes it possible to optimise for a large number of design variables. The optimisations employ either a variable-fidelity method that combines low- and high-fidelity models or a direct sequential quadratic programming (SQP) method. Four Euler optimisations of a BWB aircraft are then presented. The optimisation is allowed to change a series of master sections defining the aircraft geometry as well as the sweep angle on the outer wing for two of the optimisations. Substantial improvements are obtained, not only in the Euler mode but also when the optimised geometries are evaluated using Reynolds-averaged Navier-Stokes solutions. Some interesting features of the optimised wing profiles are discussed.

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36

Cai, Chen Fang, Yong Ming Qin i Jiang Hao Wu. "The Effect of Belly-Flap on Aerodynamic Performance of Blended Wing Body Civil Aircraft". Applied Mechanics and Materials 378 (sierpień 2013): 69–73. http://dx.doi.org/10.4028/www.scientific.net/amm.378.69.

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The effect of Belly-flap on aerodynamic performance of BWB civil aircraft are investigated in take-off and landing by computational fluid dynamics. And the overload of BWB with Belly-flap also is calculated in the same flight condition. Six parameters are discussed as design parameters of the Belly flap. It is shown that the proper combination of design parameters of Belly-flap can increase the maximum of lift and reduce the angle of attack and nose down moment to improve the flight safety in take-off and landing. When the aircraft with Belly-flap encounters the gust, the maximum overload is very close to 2.5 which are requested by FAR. It is suggested the optimized design of Belly-flap should be done if the Belly-flap is applied in BWB civil aircraft.

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37

Karpuk, Stanislav, Yaolong Liu i Ali Elham. "Multi-Fidelity Design Optimization of a Long-Range Blended Wing Body Aircraft with New Airframe Technologies". Aerospace 7, nr 7 (30.06.2020): 87. http://dx.doi.org/10.3390/aerospace7070087.

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The German Cluster of Excellence SE²A (Sustainable and Energy Efficient Aviation) is established in order to investigate the influence of game-changing technologies on the energy efficiency of future transport aircraft. In this paper, the preliminary investigation of the four game-changing technologies active flow control, active load alleviation, boundary layer ingestion, and novel materials and structure concepts on the performance of a long-range Blended Wing Body (BWB) aircraft is presented. The BWB that was equipped with the mentioned technologies was designed and optimized using the multi-fidelity aircraft design code SUAVE with a connection to the Computational Fluid Dynamics (CFD) code SU2. The conceptual design of the BWB aircraft is performed within the SUAVE framework, where the influence of the new technologies is investigated. In the second step, the initially designed BWB aircraft is improved by an aerodynamic shape optimization while using the SU2 CFD code. In the third step, the performance of the optimized aircraft is evaluated again using the SUAVE code. The results showed more than 60% reduction in the aircraft fuel burn when compared to the Boeing 777.

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Cunha, Pedro Paulo Santos Rodrigues da, Pedro Mariani Souza, Letícia Campos Valente, Gabriel Maertens Vaz de Mello i Pedro Américo Almeida Magalhães Junior. "Analysis of induced drag and vortex at the wing tip of a Blended Wing Body aircraft". International Journal of Advanced Engineering Research and Science 5, nr 6 (2018): 7–9. http://dx.doi.org/10.22161/ijaers.5.6.2.

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M Ahmad, A., R. E M Nasir, Z. A A Latif, W. Kuntjoro, W. Wisnoe i I. S Ishak. "Aerodynamic characteristics of a cranked planform blended wing-body aircraft with 400 sweep angle". International Journal of Engineering & Technology 7, nr 4.13 (9.10.2018): 37. http://dx.doi.org/10.14419/ijet.v7i4.13.21326.

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Baseline 7 Blended Wing-Body design is introduced to study the behaviour of the control surfaces, given four elevons without vertical stabilizer and wingtip. The objective of the paper is to obtain an aerodynamic characteristic of a cranked planform blended wing-body aircraft. The airfoil used for the entire body is NACA 2412, which is selected for ease of fabrication process. The wingspan of the model is 1.4 m with 0.2 m thickness. The sweep angle of the model is fixed to 400. The wingspan area is calculated at 0.405 m2. The experiment is conducted at UTM-LST Wind Tunnel, AEROLAB, Skudai, Johor with test wind speed of 15 m/s. The maximum lift-to-drag ratio for the model is found to be around 21.9, which is better than many conventional aircraft. Nonetheless, the parabolic regression made to the drag versus lift plot only yields maximum lift-to-drag ratio of 10.0. The value of drag coefficient at zero lift is 0.012 while the maximum lift coefficient found is at 0.65 at 150 angle of attack. The lift-to-drag ratio improves 38.3% from 15.9 in the previously-published design. The neutral point is found to be located at 30.6% of the mean geometric chord in front of the wind tunnel model reference center or about 0.398 m from the nose of the 0.63 m long aircraft model or at 63.1% of aircraft length from the nose.

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Ali, Zurriati Mohd, Wahyu Kuntjoro i Wisnoe Wirachman. "The Effect of Canard to the Aerodynamic Behavior of Blended Wing Body Aircraft". Applied Mechanics and Materials 225 (listopad 2012): 38–42. http://dx.doi.org/10.4028/www.scientific.net/amm.225.38.

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This paper presents a study on the effect of canard setting angle on the aerodynamic characteristic of a Blended Wing Body (BWB). Canard effects to BWB aerodynamic characteristics are not widely investigated. Hence the focus of the study is to investigate the variations of lifts, drags and moments when the angles of attack are varied at different canard setting angles. Wind tunnel tests were performed on BWB aircraft with canard setting angles,  ranging from -20˚ to 20˚. Angles of attack,  were varied from -10˚ to 10˚. Aspect ratio and canard planform area were kept fixed. All tests were conducted in the subsonic wind tunnel at Universiti Teknologi MARA, at Mach number of 0.1. The streamlines flow, at the upper surface of the canard was visualized using mini tuft. Result shows that the lift coefficient does not change much with different canard setting angles. As expected, the lift coefficient increases with increasing angles of attack at any canard setting angle. In general, the moment coefficient increases as the canard setting angle is increased. The results obtained in this research will be of importance to the understanding of aerodynamic behavior of BWB employing canard in its configuration.

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Mohr, B., D. Paulus, H. Baier i M. Hornung. "Design of a 450-passenger blended wing body aircraft for active control investigations". Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 226, nr 12 (21.12.2011): 1513–22. http://dx.doi.org/10.1177/0954410011426031.

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CHEN, Zhenli, Minghui ZHANG, Yingchun CHEN, Weimin SANG, Zhaoguang TAN, Dong LI i Binqian ZHANG. "Assessment on critical technologies for conceptual design of blended-wing-body civil aircraft". Chinese Journal of Aeronautics 32, nr 8 (sierpień 2019): 1797–827. http://dx.doi.org/10.1016/j.cja.2019.06.006.

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Huijts, Crispijn, i Mark Voskuijl. "The impact of control allocation on trim drag of blended wing body aircraft". Aerospace Science and Technology 46 (październik 2015): 72–81. http://dx.doi.org/10.1016/j.ast.2015.07.001.

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Sgueglia, Alessandro, Peter Schmollgruber, Emmanuel Benard, Nathalie Bartoli i Joseph Morlier. "Preliminary Sizing of a Medium Range Blended Wing-Body using a Multidisciplinary Design Analysis Approach". MATEC Web of Conferences 233 (2018): 00014. http://dx.doi.org/10.1051/matecconf/201823300014.

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The aviation's goal for the next decades is to drastically reduce emissions, but to achieve this goal a breakdown in aircraft design has to be considered. One of the most promising concepts is the Blended Wing- Body, which integrates aerodynamics, propulsion and structure, and has a better aerodynamics efficiency, thanks to the reduction of the wetted surfaces. In this work the feasibility of a short/medium range BWB with 150 passengers (A320 Neo type aircraft, Entry Into Service 2035) is studied, considering different disciplines into the sizing process. The design loop has been reviewed to consider the unconventional concept. Also certification aspects have been taken into account in an off-design analysis. To evaluate the advantages of the proposed concept, it has been compared with an aircraft of the same class, the A320 Neo, resized to match the EIS2035 hypothesis: results show that the BWB is a concept that demonstrates a gain in fuel consumption, especially on longer ranges.

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Kumar, Ashutosh, i Raghvendra Gautam. "Design of Elevons, Wings, and Performance Investigation for A Blended Wing Body UAV". International Journal of Engineering and Advanced Technology 11, nr 1 (30.10.2021): 60–69. http://dx.doi.org/10.35940/ijeat.a3152.1011121.

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Objectives: To study a hybrid VTOL- Blended wing body design for its wings and elevons and perform CFD simulations with the wings. The steps for designing wing configuration and Elevon positioning involve different variables giving rise to a large number of design possibilities for a control surface. In the current study methods, have been proposed for the selection of optimized wing configuration and elevons positioning and validated with simulations model. Methods: Meta-heuristic methods like genetic algorithms are used for arriving at favorable solutions and Matlab coding is written for the initial draft of wing geometry, selected geometries are iterated in XFLR5 for stability and control, and later validated with simulations around the fluid domain. Elevons are control surfaces generally installed in tailless aircraft at the wing's trailing edge. It applies to roll and pitching force to wings as it combines the functionality of both pitching and rolling control. Design space was mathematically plotted and solved using MATLAB to decide elevons, wing configuration, and their positions.Findings: Initial selection of wing geometry, aoa, and structural design for maneuverability and stability for the enhanced aerodynamic performance of BWB UAV. In this presented paper drag coefficient of the designed BWB UAV comes out to be precisely around 0.02216 using computational modeling. Variation curve of Lift and drag coefficient with aspect ratio and angle of attack. Post-processing results of pressure forces and velocity profile on Wings accurately validate the proposed method of control surface optimization. Novelty: Designed BWB UAV has increased lift to drag ratio, reduced weight of airframe which improves performance. The Design phase is highly iterative, Through this research paper, an attempt has been made to develop a methodology for selection and investigation of control surfaces against requirements that makes BWB UAV more helpful for practical use and increasing the lift and endurance efficiency of the hybrid VTOL- Blended wing body aircraft.

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Siouris, S., i N. Qin. "Study of the effects of wing sweep on the aerodynamic performance of a blended wing body aircraft". Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 221, nr 1 (styczeń 2007): 47–55. http://dx.doi.org/10.1243/09544100jaero93.

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Mohamad, Firdaus, Wisnoe Wirachman, Wahyu Kuntjoro i 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 (styczeń 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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Wong, W. S., A. Le Moigne i N. Qin. "Parallel adjoint-based optimisation of a blended wing body aircraft with shock control bumps". Aeronautical Journal 111, nr 1117 (marzec 2007): 165–74. http://dx.doi.org/10.1017/s0001924000004425.

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An Euler optimisation for a BWB configuration with winglets incorporating an array of three-dimensional shock control bumps is carried out by employing an efficient adjoint-based optimisation methodology. A high fidelity multi-block grid with over two million grid points is generated to resolve the shape of the 3D shock control bumps, the winglet as well as the overall BWB shape, which are parameterised by over 650 design variables. In order to perform such a large aerodynamic optimisation problem feasibly, the optimisation tools such as the flow solver and the adjoint solver have to be parallelised with a good parallel efficiency. This paper reports the parallel implementation efforts on the adjoint solver; especially on the calculation of the sensitivity derivatives, which has to be looped over the total number of design variables. Results from the optimisation of the wing master sections, winglet aerofoil sections and the three dimensional bumps indicate a significant improvement regarding the aerodynamic performance against the baseline geometry for the given planform layout of the aircraft.

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Lee, Sea-Wook, Jin-Yeol Yang i Jin-Soo Cho. "Aerodynamic Analysis of an Arbitrary Three-Dimensional Blended Wing Body Aircraft using Panel Method". Journal of the Korean Society for Aeronautical & Space Sciences 37, nr 11 (1.11.2009): 1066–72. http://dx.doi.org/10.5139/jksas.2009.37.11.1066.

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Ammar, Sami, Clément Legros i Jean-Yves Trépanier. "Conceptual design, performance and stability analysis of a 200 passengers Blended Wing Body aircraft". Aerospace Science and Technology 71 (grudzień 2017): 325–36. http://dx.doi.org/10.1016/j.ast.2017.09.037.

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