Relevant bibliographies by topics / Dihedral angle control

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Academic literature on the topic 'Dihedral angle control'

Author: Grafiati
Published: 4 June 2025
Last updated: 6 July 2025

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Journal articles on the topic "Dihedral angle control"

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Kinuta, Takafumi, Nobuo Tajima, Michiya Fujiki, Mitsuo Miyazawa, and Yoshitane Imai. "Control of circularly polarized photoluminescent property via dihedral angle of binaphthyl derivatives." Tetrahedron 68, no. 24 (2012): 4791–96. http://dx.doi.org/10.1016/j.tet.2012.03.119.

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Nicy and David J. Wales. "Energy Landscapes and Heat Capacity Signatures for Monomers and Dimers of Amyloid-Forming Hexapeptides." International Journal of Molecular Sciences 24, no. 13 (2023): 10613. http://dx.doi.org/10.3390/ijms241310613.

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Amyloid formation is a hallmark of various neurodegenerative disorders. In this contribution, energy landscapes are explored for various hexapeptides that are known to form amyloids. Heat capacity (CV) analysis at low temperature for these hexapeptides reveals that the low energy structures contributing to the first heat capacity feature above a threshold temperature exhibit a variety of backbone conformations for amyloid-forming monomers. The corresponding control sequences do not exhibit such structural polymorphism, as diagnosed via end-to-end distance and a dihedral angle defined for the monomer. A similar heat capacity analysis for dimer conformations obtained using basin-hopping global optimisation shows clear features in end-to-end distance versus dihedral correlation plots, where amyloid-forming sequences exhibit a preference for larger end-to-end distances and larger positive dihedrals. These results hold true for sequences taken from tau, amylin, insulin A chain, a de novo designed peptide, and various control sequences. While there is a little overall correlation between the aggregation propensity and the temperature at which the low-temperature CV feature occurs, further analysis suggests that the amyloid-forming sequences exhibit the key CV feature at a lower temperature compared to control sequences derived from the same protein.
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Pan, Tianyu, Kaikai Shi, Hanan Lu, Zhiping Li, and Jian Zhang. "Numerical Investigations of a Non-Uniform Stator Dihedral Design Strategy for a Boundary Layer Ingestion (BLI) Fan." Energies 15, no. 16 (2022): 5791. http://dx.doi.org/10.3390/en15165791.

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A distributed propulsion system has the advantage of saving 5–15% fuel burn through ingesting the fuselage boundary layer of an aircraft by fan or compressor. However, due to boundary layer ingestion (BLI), the fan stage will continuously operate under serious inlet distortion. This will lead to a circumferentially non-uniform flow separation distribution on the stator blade suction surface along the annulus, which significantly decreases the fan’s adiabatic efficiency. To solve this problem, a non-uniform stator dihedral design strategy has been developed to explore its potential of improving BLI fan performance. First, the stator full-annulus blade passages were divided into blade dihedral design regions and baseline design regions on the basis of the additional aerodynamic loss distributions caused by BLI inlet distortion. Then, to find the appropriate dihedral design parameters, the full-annulus BLI fan was discretized into several portions according to the rotor blade number and the dihedral design parameter investigations for dihedral depth and dihedral angle were conducted at the portion with the largest inflow distortion through a single-blade-passage computational model. The optimal combinational dihedral design parameter (dihedral depth 0.3, dihedral angle 6 deg) was applied to the blade passages with notable flow loss which were mainly located in the annulus positions from −120 to 60 degrees suffering from inlet distortion, while the blades in the low-loss annulus locations were unchanged. In this way, a non-uniform stator dihedral design scheme was achieved. In the end, the effectiveness of the non-uniform stator dihedral design was validated by analyzing the internal flow fields of the BLI fan. The results show that the stator dihedral design in distorted regions can increase the inlet axial velocity and reduce the aerodynamic load near the blade trailing edge, which are beneficial for suppressing the flow separations and reducing aerodynamic loss. Specifically, compared with the baseline design, the non-uniform stator dihedral design has achieved a reduction of aerodynamic loss of about 7.7%. The fan stage has presented an improvement of adiabatic efficiency of about 0.48% at the redesigned point without sacrificing the total pressure ratio. In the entire operating range, the redesigned fan has also shown a higher adiabatic efficiency than the baseline design with no reduction of the total pressure ratio, which provides a probable guideline for future BLI distortion-tolerant fan design.
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Mori, Hatsumi, Naoki Sakurai, Shoji Tanaka та ін. "Control of Electronic State by Dihedral Angle in θ-type Bis(ethylenedithio)tetraselenafulvalene Salts". Chemistry of Materials 12, № 10 (2000): 2984–87. http://dx.doi.org/10.1021/cm000321+.

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Yoshida, Naoya, Tomoya Ishizuka, Atsuhiro Osuka, et al. "Fine Tuning of Photophysical Properties of mesomeso-Linked ZnII–Diporphyrins by Dihedral Angle Control." Chemistry - A European Journal 9, no. 1 (2003): 58–75. http://dx.doi.org/10.1002/chem.200390004.

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Li, Peilin. "Analysis of Combination of Four, Five Six Crease Vertices Waterbomb." Highlights in Science, Engineering and Technology 18 (November 13, 2022): 59–66. http://dx.doi.org/10.54097/hset.v18i.2569.

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Origami combination is reliable because of great stabilization and controllable deployable. Potential and extensive applied in medical field, as a soft robot gripper. To investigate a possible stabilization structure, this design contained a combination of three four-crease vertexes, one five-crease vertex and one six-crease vertex. The design theory is based on waterbomb pattern design and obey the two design principles. The degree of freedom in this combination would be proof is zero, which demonstrates an over-constrained structure, and also the poor control performance and reliability. The reason might be the compelling in five-crease vertex and multiple Dof in the four-crease vertexes (which might be one Dof), which cause the overall outputs dihedral angles could not be controlled by overall inputs. Additionally, this design has faster equilibrium state because of smaller dihedral angle (smaller than 90 degrees) in each vertex, as an overstrained structure. The future improvement might be done by reduce the Dof in the four-crease vertex and promotion in five-crease vertex.
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Byakova, A. V., YU V. Milman, and A. A. Vlasov. "Application of the plasticity characteristic determined by the indentation technique for evaluation of mechanical properties of coatings: II. guidelines to coating development and processing control." Science of Sintering 36, no. 2 (2004): 93–103. http://dx.doi.org/10.2298/sos0402093b.

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The equilibrium between solid and 1iquid phases in sintered composite materials has been studied. It is shown that closed surfaces, which bound dispersed phases, influence the mechanical equilibrium between these phases. An expression is derived for a dihedral angle in composite materials, which includes values of surface tensions at the phase interfaces as well as parameters of a composite equilibrium structure (phase composition, particle contiguity and coefficients of a particle geometry). .
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Yoshida, Naoya, and Atsuhiro Osuka. "Control of Dihedral Angle of Meso−Meso Linked Diporphyrins by Introducing Dioxymethylene Straps of Various Length." Organic Letters 2, no. 19 (2000): 2963–66. http://dx.doi.org/10.1021/ol006216n.

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Ahn, Tae Kyu, Kil Suk Kim, Deok Yun Kim та ін. "Relationship between Two-Photon Absorption and the π-Conjugation Pathway in Porphyrin Arrays through Dihedral Angle Control". Journal of the American Chemical Society 128, № 5 (2006): 1700–1704. http://dx.doi.org/10.1021/ja056773a.

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Dharmapurikar, Satej S., Sundaresan Chithiravel, Manoj V. Mane, Gunvant Deshmukh, and Kothandam Krishnamoorthy. "Dihedral angle control to improve the charge transport properties of conjugated polymers in organic field effect transistors." Chemical Physics Letters 695 (March 2018): 51–58. http://dx.doi.org/10.1016/j.cplett.2018.01.052.

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Books on the topic "Dihedral angle control"

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M, Ware George, and Langley Research Center, eds. Control effectiveness and tip-fin dihedral effects for the HL-20 lifting-body configuration at Mach numbers from 1.6 to 4.5. National Aeronautics and Space Administration, Langley Research Center, 1995.

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Conference papers on the topic "Dihedral angle control"

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Fei, Teng, Lucheng Ji, and Weilin Yi. "Investigation of the Dihedral Angle Effect on the Boundary Layer Development Using Special-Shaped Expansion Pipes." In ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/gt2018-76383.

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The corners between the blades and end walls are common geometric structures in turbomachinery, where boundary layers on the blade and end wall surface interact with each other. This boundary layer interaction enlarges the region of low momentum fluid which leads to the boundary layers grow thicker at the corner region. Then the corner separation is likely to occur, and even worse by the adverse pressure gradient along the streamwise as well as secondary flows along the pitchwise. The key issue to design the geometric structures of the corner region is to control the dihedral angle between the blade and end wall surface. However, from the current published literature, few researchers have studied the influence of dihedral angle on the flow structures at the corner region in detail. In this paper, a series of expansion pipes with different cross sections which represent different dihedral angles are simulated. Then, some useful conclusions about how the dihedral angle affects the flow structures at the corner region are drawn. Moreover, a new method to predict the boundary layer thickness at the corner region is introduced, and the predicted results are in good agreement with simulation results.
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Guggilla, Mukesh, and Vijayakumar Rajagopalan. "CFD Investigation on the Hydrodynamic Characteristics of Blended Wing Unmanned Underwater Gliders With Emphasis on the Control Surfaces." In ASME 2020 39th International Conference on Ocean, Offshore and Arctic Engineering. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/omae2020-19280.

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Abstract Underwater Gliders are unique buoyancy propelled oceanographic profiling vehicles. Their speed and endurance in longitudinal motion are affected by the symmetry, sweep dihedral angle and span of the control surfaces. In the low-velocity regime, these parameters can be varied to examine the flow around the glider. They also affect the lift-to-drag ratio (L/D) essential for the manoeuvring path in longitudinal and transverse motions. In this paper, the sweep angle of the main wing of a blended wing autonomous underwater glider configuration is varied as 10°, 15°, 30°, 45° and 60° and the resulting hull forms are numerically simulated in the commercial software, STARCCM+. The main wing is a tapered NACA0018 section (taken as per the general arrangement requirement) with 1.5m chord at the root and 0. 1m at the tip. The numerical model is validated using the CFD results of NACA0012 airfoil from Sun.C et al, 2015 [1]. The hydrodynamic forces are obtained by varying the angle of attack (α) of the body from −15° to 15°, for flow velocity of 0.4m/s. The hydrodynamic coefficients (lift-to-drag ratios) and flow physics around the wing are analyzed to arrive at an optimum Lift-to-drag ratio for increased endurance.
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Li, Jiabin, Lucheng Ji, and Weilin Yi. "The Use of Blended Blade and End Wall in Compressor Cascade: Optimization Design and Flow Mechanism." In ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/gt2018-76048.

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Nowadays, the flow field at the compressor is more and more complex with the increasing of the aerodynamic loading. The complex flow in the endwall regions is thus key to aerodynamic blockage, loss production, and finally its performance deterioration. The design of Blended Blade and End Wall (BBEW) contouring technology had been proved to be useful in delaying, reducing, and eliminating the corner separation in the compressor. The BBEW technology can adjust the dihedral angle between the suction and the endwall in 30% of the spanwise easily, which is different with the fillet. However, the design of the BBEW always relies on the experiences of the designers, and the effective design results cannot be the optimal result. This paper presents an optimization design method for the BBEW technology, and analyses the flow mechanism of the BBEW design. Firstly, the parameters for the BBEW design is simplified as two, one is the maximum blended width, the other is the axial position of the maximum blended width. The optimal result can be obtained through the response surface method. Secondly, based on the optimization method, this paper make an optimization BBEW design at the suction side of a NACA65 linear compressor cascade with the turning angle 42 degrees. The numerical results show that the optimal BBEW design can eliminate the boundary layer separation at the corner intersection region, and reduce the suction side separation. When the incidence angle is 0 degrees, the BBEW technology can reduce the total pressure loss coefficient by 5%, and reduce the aerodynamic blockage coefficient by 14%. The aerodynamic performance of the cascade shows a more obvious improvement with the BBEW design at a larger incidence. The total pressure loss coefficient of the cascade is reduced by 20% at 15 degrees incidence. The numerical study shows that the design with the BBEW can control the axial development of the dihedral angle between the suction side and the endwall, which can eliminate the boundary layer separation at the corner intersection region. What’s more, the BBEW technology can produce a pressure gradient at the axial position of the maximum blended width, and value of the pressure gradient in proportion to the maximum blended width. This pressure gradient enhance the kinetic energy of the low energy fluid at the endwall region, which is consist of the secondary cross flow, thus elevating the capability to withstand the adverse pressure gradient, and improve the suction side separation around the trailing edge.
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Zhu, Huiling, Ling Zhou, Jiabin Li, Tongtong Meng, and Lucheng Ji. "LARGE EDDY SIMULATION OF CORNER STALL CONTROL IN A LINEAR COMPRESSOR CASCADE BY BLENDED BLADE AND ENDWALL TECHNIQUE." In GPPS Xi'an21. GPPS, 2022. http://dx.doi.org/10.33737/gpps21-tc-188.

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Under the influence of a strong adverse pressure gradient, secondary flow, and other factors, compressor cascades are prone to corner separation, and even leading to corner stall, which seriously affects aerodynamic performance. In this paper, large eddy simulation is used to investigate the effects and mechanisms of corner stall controlled by the blended blade and endwall technique. The suction side root of a modified NACA65 blade is designed by this technique. The results show that the corner stall topology is changed, in which a single large separation vortex on the endwall is weakened and broken into two small separation vortices, and the spanwise and pitchwise ranges of corner separation are reduced. Most importantly, the total pressure loss coefficient is reduced compared with the prototype cascade. All above prove that the blened blade and endwall technique can control corner stall in the compressor cascade to a certain extent. The underlying physical mechanisms are as follows: by increasing the dihedral angle, the intersection of the boundary layers and the development of the corner vortex are obviously suppressed. Moreover, the axial and spanwise forces generated by the technique can increase the kinetic energy of the surrounding fluid and transport the low-energy fluid upward to reduce accumulation on the endwall respectively.
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Meng, Tongtong, Lucheng Ji, Xin Li, Jiabin Li, and Zhou Ling. "Numerical Investigations on Full Blended Blade and Endwall Technique." In ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-16136.

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Abstract In present state of art, compressor blades can work efficiently between the span of 20%–80%, while nearly 30% of the total loss comes from endwall region. Previous studies have shown that Blended Blade and End Wall (BBEW) which is a control technique can reduce the corner separation effectively. To further reduce the loss, enhance diffusion capability and restrain the secondary flow in the endwall region, in addition of a kind of non-axisymmetric endwall, Full-BBEW technique is put forward. Firstly, the geometric method of the Full-BBEW technique is presented on a NACA65 cascade with the unchanged axial passage area. Moreover, under the category of Full-BBEW technique, according to the different geometry characteristic, BBEW (blended blade and endwall) model, IOEW (inclining-only hub) model and Full-BBEW model are presented. Then in order to find the most effective design, numerical investigation and optimization based on the Kriging surrogate model are employed on the models. Compared with the prototype, the total pressure loss coefficient decreases by 7%–9% in optimized Full-BBEW cases and the aerodynamic blockage coefficient decreases about 23%–36%. Through analysis, the blended blade geometry creates a radial pressure gradient at the end section and push the low-energy fluid up to the mainstream. As the result, the loss decreases significantly between 5%–25% span range. Meanwhile, the intersection of boundary layer weakens because of the expanded dihedral angle. On the other hand, the inclining-only hub geometry reduces the circumferential pressure gradient and restrains the crossflow in corner. Overall, though the loss in mainstream increases slightly, Full-BBEW technique can reduce the boundary layer intersection and the crossing flow in corner so that the diffusion capability further increases and the aerodynamic performance in the endwall region improves effectively.
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Clarke, Matthew A., Narcrisha S. Norman, and Sonya T. Smith. "Hybrid-MCX-1, BWB and 777 Aircraft Comparison." In ASME 2015 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/imece2015-52526.

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Conceptual design is the first and most important phase of an aircraft’s configuration and system development process. That being said, there is no denying that innovation in aviation has stunted over the last 50 years; the once every present fascination of flying has been blanketed by the rapid profit-driven commercializing of an industry. Moreover, we have reached an apex of maximizing the efficiency of current passenger aircraft model configurations. In recent times, new research and development has culminated to the introduction of aerodynamic structures to address key issues such as stability and fuel efficiency. This research paper seeks to push the envelope of innovation with a brand new perspective on how we view air travel — redefining the Why, What and How. It explores novel concepts such as Boeing Blended Wing Body (BWB) aircraft shown in, which does not follow the conventional Tube and Wing (TAW) configuration. It is a tailless design that integrates the wing and the fuselage into a single-lifting surface. The most common advantages include a higher lift-to-drag ratio and higher payload capacity due to a distribute load along the centerline of the aircraft. On the other hand, a tailless configuration comes at a cost to in-flight maneuvering and stability. The unique design of the Hybrid-MCX-1 aircraft involves the application of the active aero-elastic tailoring to aircraft topology optimization for both subsonic and transonic regimes. With a focus on experimental wind tunnel testing and high-fidelity simulations, this project proposes a new concept that deviates from today’s tubular and wing concept. The aircraft has a unique shape with a forward fuselage that starts off with the conventional tubular and winged aircraft design currently flown in commercial travel, but deviates to a wider cross section at the center of the fuselage. The model has self-supporting, cantilever, dihedral, swept wings, with pronounced fillets at the junction of the wing root and fuselage, blending them smoothly. This smooth transition reduce interference between airflow over the wing root and the adjacent body surface, ultimately reducing drag. The engines of the Hybrid-MCX-1 are mounted by at 45-degree angle on the rear of the plane. This engine location offers the opportunity for swallowing the boundary layer of air from that portion of the center body upstream of the inlet, providing improved propulsive efficiency by reducing the ram drag. The Hybrid-MCX-1 also possesses a vertical tail that bisects the engines. As with current commercial aircraft, this tail provides lateral stability and controls the yaw. In the case of the BWB, yaw control is made possible by sweeping the wing and downloading the wingtips. However, this approach reduces the effective aerodynamic wingspan of the aircraft and imposes a significant induced drag penalty. The presence of a tail on the concept model addresses the aforementioned issue and rectifies unwanted yawing that may arise during cross wind flight conditions. The rear end of the aircraft decrease significantly in vertical thickness when compared to the lateral thickness to minimize the possibility of flow separation as air passes around the wings and over the front half of the aircraft while maximizing total lifting surface area. The pylons are adequately sized to avoid aerodynamic interference between fuselage, pylon and nacelle but still relatively short to minimize drag.
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