Relevant bibliographies by topics / Sharp leading edges

Contents

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

Academic literature on the topic 'Sharp leading edges'

Author: Grafiati
Published: 4 June 2021
Last updated: 1 February 2022

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Journal articles on the topic "Sharp leading edges"

1

Jin, Xinxin, Rujie He, Xinghong Zhang, and Ping Hu. "Ablation behavior of ZrB2–SiC sharp leading edges." Journal of Alloys and Compounds 566 (July 2013): 125–30. http://dx.doi.org/10.1016/j.jallcom.2013.03.067.

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He, Ru Jie, Xing Hong Zhang, and Ping Hu. "Ablation Property of ZrB2-SiC Composite Sharp Leading Edges with Varying Radiuses of Curvature under Oxy-Acetylene Torch." Key Engineering Materials 512-515 (June 2012): 710–14. http://dx.doi.org/10.4028/www.scientific.net/kem.512-515.710.

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Ablation behavior of ZrB2-SiC sharp leading edges with five different curvature radiuses was investigated using an oxy-acetylene torch. During the test, the curvature radiuses were 0.15 mm, 0.5 mm, 1.0 mm, 1.5 mm, and 2.0 mm, respectively. Under the same ablation condition, the smaller was the radius, the severer ablation underwent. The sharp leading edge with a curvature radius of 0.15 mm had the highest surface temperature and maximum surface temperature rising rate, exceeded 2100°C in less than 30 s. However, the surface of sharp leading edge with a curvature radius of 2.0 mm achieved only 1900°C in more than 60 s. After 5 min ablation, the mass and linear ablation rates were measured. All the five sharp leading edges evolved to nearly a same radius after ablation. The microstructure of the oxidation layers was also investigated. A ZrO2-SiO2 layer generated from oxidation of ZrB2-SiC acts as a thermal barrier and reduces the diffusion of oxygen.
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Monteverde, Frédéric, and Raffaele Savino. "ZrB2-SiC Sharp Leading Edges in High Enthalpy Supersonic Flows." Journal of the American Ceramic Society 95, no. 7 (May 8, 2012): 2282–89. http://dx.doi.org/10.1111/j.1551-2916.2012.05226.x.

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Monti, Rodolfo, Raffaele Savino, and Mario De Stefano Fumo. "Matching Flight Conditions on Sharp Leading Edges in Plasma Wind Tunnels." Journal of Thermophysics and Heat Transfer 21, no. 3 (July 2007): 660–64. http://dx.doi.org/10.2514/1.26465.

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Sriram, R., L. Srinath, Manoj Kumar K. Devaraj, and G. Jagadeesh. "On the length scales of hypersonic shock-induced large separation bubbles near leading edges." Journal of Fluid Mechanics 806 (September 30, 2016): 304–55. http://dx.doi.org/10.1017/jfm.2016.591.

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The interaction of a hypersonic boundary layer on a flat plate with an impinging shock – an order of magnitude stronger than that required for incipient separation of the boundary layer – near sharp and blunt leading edges (with different bluntness radii from 2 to 6 mm) is investigated experimentally, complemented by numerical computations. The resultant separation bubble is of length comparable to the distance of shock impingement from the leading edge, rather than the boundary layer thickness at separation; it is termed large separation bubble. Experiments are performed in the IISc hypersonic shock tunnel HST-2 at nominal Mach numbers 5.88 and 8.54, with total enthalpies 1.26 and $1.85~\text{MJ}~\text{kg}^{-1}$ respectively. Schlieren flow visualization using a high-speed camera and surface pressure measurements using fast response sensors are the diagnostics. For the sharp leading edge case, the separation length was found to follow an inviscid scaling law according to which the scaled separation length $(L_{sep}/x_{r})M_{er}^{3}$ is found to be linearly related to the reattachment pressure ratio $p_{r}/p_{er}$; where $L_{sep}$ is the measured separation length, $x_{r}$ the distance of reattachment from the leading edge, $M$ the Mach number, $p$ the static pressure and the subscripts $r$ and $e$ denote the conditions at the reattachment location and at the edge of the boundary layer at the shock impingement location respectively. However, for all the blunt leading edges $(L_{sep}/x_{r})M_{er}^{3}$ was found to be a constant irrespective of Mach number and much smaller than the sharp leading edge cases. The possible contributions of viscous and non-viscous mechanisms towards the observed phenomena are explored.
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Jones, Kevin D., and F. Carroll Dougherty. "Numerical simulations of high-speed flows about waveriders with sharp leading edges." Journal of Spacecraft and Rockets 29, no. 5 (September 1992): 661–67. http://dx.doi.org/10.2514/3.11507.

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Zeng, Yan. "Drag Reduction for Sweptback Grid Fin with Blunt and Sharp Leading Edges." Journal of Aircraft 49, no. 5 (September 2012): 1526–31. http://dx.doi.org/10.2514/1.c031653.

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Wang, Anzhe, Ping Hu, Bin Du, Cheng Fang, Dongyang Zhang, and Xinghong Zhang. "Cracking behavior of ZrB2-SiC-Graphite sharp leading edges during thermal shock." Ceramics International 44, no. 7 (May 2018): 7694–99. http://dx.doi.org/10.1016/j.ceramint.2018.01.195.

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Buzica, Andrei, Lisa Debschütz, Florian Knoth, and Christian Breitsamter. "Leading-Edge Roughness Affecting Diamond-Wing Aerodynamic Characteristics." Aerospace 5, no. 3 (September 19, 2018): 98. http://dx.doi.org/10.3390/aerospace5030098.

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Diamond wing configurations for low signature vehicles have been studied in recent years. Yet, despite numerous research on highly swept, sharp edged wings, little research on aerodynamics of semi-slender wings with blunt leading-edges exists. This paper reports on the stall characteristics of the AVT-183 diamond wing configuration with variation of leading-edge roughness size and Reynolds number. Wind tunnel testing applying force and surface pressure measurements are conducted and the results presented and analysed. For the investigated Reynolds number range of 2.1 × 10 6 ≤ R e ≤ 2.7 × 10 6 there is no significant influence on the aerodynamic coefficients. However, leading-edge roughness height influences the vortex separation location. Trip dots produced the most downstream located vortex separation onset. Increasing the roughness size shifts the separation onset upstream. Prior to stall, global aerodynamic coefficients are little influenced by leading-edge roughness. In contrast, maximum lift and maximum angle of attack is reduced with increasing disturbance height. Surface pressure fluctuations show dominant broadband frequency peaks, distinctive for moderate sweep vortex breakdown. The experimental work presented here provides insights into the aerodynamic characteristics of diamond wings in a wide parameter space including a relevant angle of attack range up to post-stall.
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Debiasi, Marco, and Yan Zeng. "Forces and Moments Generated by Swept-Back Grid Fins with Sharp Leading Edges." Journal of Aircraft 53, no. 6 (November 2016): 1964–68. http://dx.doi.org/10.2514/1.c033504.

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Dissertations / Theses on the topic "Sharp leading edges"

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Gien, Kuo-Don, and 簡國棟. "Investigation on Flow Characteristics of Statics and Dynamics of Sharp Leading Edge Model at High Angle of Attack." Thesis, 2006. http://ndltd.ncl.edu.tw/handle/42917072592832538053.

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碩士
國立中興大學
機械工程學系
94
The purpose of this thesis is to study the observed characteristics of high angle of attack of sharp leading edge flat model both in the static and dynamic condition by applying water tunnel fluid. Also compare them with outboard leading edge. The experiment is to set up specimen position with side slip angle (β=0°~10°), pitch up angle (α=0°~ 50°), and dynamic pitch rate in pitch-up and pitch-down process. From the result of flow field by applying dye release method, the findings show that in the static condition, vortex burst position of flat model will move closer to the front of wing if increasing the pitch-up angle. The position of vortex burst is basically symmetric in both sides of the wing. Nevertheless, there is a vortex burst delay in dynamic situation. If increase sideslip angle, the windward vortex burst will collapse in advance. Also under the same condition, vortex burst will delay more seriously for pitch-up than pitch-down processes. The delay will be more obvious for increasing pitch rate. Also, in this study, we compare different effects between the outboard leading edge model and sharp leading edge model.
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DING, ZHI-HUA, and 丁志華. "Simulation of sharp leading-edge and side-edge vortex separation of a low-aspect-ratio wing at high angle of attack in subsonic flow." Thesis, 1988. http://ndltd.ncl.edu.tw/handle/81917943210256121009.

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Books on the topic "Sharp leading edges"

1

Hoeijmakers, H. W. M. Numerical simulation of leading-edge vortex flow. Amsterdam, Netherlands: National Aerospace Laboratories, 1991.

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2

Tavella, Domingo A. The lift of sharp-leading-edged delta wings with blowing. Stanford, Calif: Stanford University, Dept. of Aeronautics and Astronautics, 1985.

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E, Glass David, and Langley Research Center, eds. Fabrication and testing of a leading-edge-shaped heat pipe. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1998.

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Center, Langley Research, ed. Supersonic leading edge receptivity. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1998.

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5

Joint Institute for Aeronautics and Acoustics., ed. The art of sharp-leading-edged delta wings with blowing. Stanford, CA: Stanford University, Dept. of Aeronautics and Astronautics, 1985.

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Joint Institute for Aeronautics and Acoustics., ed. The art of sharp-leading-edged delta wings with blowing. Stanford, CA: Stanford University, Dept. of Aeronautics and Astronautics, 1985.

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M, Darden Christine, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., eds. Applicability of linearized-theory attached-flow methods to design and analysis of flap systems at low speeds for thin swept wings with sharp leading edges. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1987.

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M, Darden Christine, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., eds. Applicability of linearized-theory attached-flow methods to design and analysis of flap systems at low speeds for thin swept wings with sharp leading edges. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1987.

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Joint Institute for Aeronautics and Acoustics, ed. The lift of sharp-leading-edged delta wings with blowing. Stanford, CA: Stanford University, Dept. of Aeronautics and Astronautics, 1985.

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Joint Institute for Aeronautics and Acoustics, ed. The lift of sharp-leading-edged delta wings with blowing. Stanford, CA: Stanford University, Dept. of Aeronautics and Astronautics, 1985.

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Book chapters on the topic "Sharp leading edges"

1

Furman, Andrej, and Christian Breitsamter. "Delta Wing Steady Pressure Investigations for Sharp and Rounded Leading Edges." In New Results in Numerical and Experimental Fluid Mechanics V, 77–84. Berlin, Heidelberg: Springer Berlin Heidelberg, 2006. http://dx.doi.org/10.1007/978-3-540-33287-9_10.

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Purwar, Anupam. "Thermo-structural Design of Hypersonic Vehicle Sharp Leading Edges for Thermo-erosive Stability Using Finite Element Modelling." In 31st International Symposium on Shock Waves 2, 1027–34. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-319-91017-8_128.

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Schreyer, A. M., W. Würz, E. Krämer, A. Talamelli, and H. Alfredsson. "Experimental Flow Studies on Separation and Reattachment in the Vicinity of Sharp,Wedge Shaped Leading Edges at Low Reynolds Numbers." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 273–80. Berlin, Heidelberg: Springer Berlin Heidelberg, 2010. http://dx.doi.org/10.1007/978-3-642-14243-7_34.

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Peng, Jinlong, Rushen Yang, Guosheng Lin, and Dongbin Ou. "Study on Heat Flux Identification and Measurement Method for the Stagnation Point of Sharp Leading Edge Model in Arc-Heated Wind Tunnel." In Lecture Notes in Electrical Engineering, 907–14. Singapore: Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-3305-7_71.

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Sonber, J. K., T. S. R. Ch. Murthy, C. Subramanian, R. C. Hubli, and A. K. Suri. "Processing Methods for Ultra High Temperature Ceramics." In MAX Phases and Ultra-High Temperature Ceramics for Extreme Environments, 180–202. IGI Global, 2013. http://dx.doi.org/10.4018/978-1-4666-4066-5.ch006.

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Ultra-high-temperature ceramics (UHTCs) are a group of materials that can withstand ultra high temperatures (1600-3000 oC) which will be encountered by future hypersonic re-entry vehicles. Future re-entry vehicles will have sharp edges to improve flight performance. The sharp leading edges result in higher surface temperature than that of the actual blunt edged vehicles that could not be withstood by the conventional thermal protection system materials. To withstand the intense heat generated when these vehicles dip in and out of the upper atmosphere, UHTC materials are needed. UHTC materials are composed of borides of early transition metals. From the larger list of borides, ZrB2 and HfB2 have received the most attention as potential candidates for leading edge materials because their oxidation resistance is superior to that of other borides due to the stability of the ZrO2 and HfO2 scales that form on these materials at elevated temperatures in oxidizing environments. Processing of these materials is very difficult as these materials are very refractory in nature. In this chapter, processes available for powder synthesis, fabrication of dense bodies, and coating processes is discussed.
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"Teaching and Leading on the Sharp Edge of Change." In The Sharp Edge of Educational Change, 15–38. Routledge, 2014. http://dx.doi.org/10.4324/9781315870724-9.

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"Monte Carlo Simulation of Flow into Channel with Sharp Leading Edge." In Rarefied Gas Dynamics: Theoretical and Computational Techniques, 582–96. Washington DC: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/5.9781600865923.0582.0596.

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Hoddeson, Lillian, and Peter Garrett. "Solar Energy: Working at the Edge of Feasibility (1979–2007)." In The Man Who Saw Tomorrow, 171–86. The MIT Press, 2018. http://dx.doi.org/10.7551/mitpress/9780262037532.003.0009.

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Ovshinsky was not the inventor of thin-film amorphous silicon solar cells, but under his direction ECD greatly improved their efficiency and dramatically lowered their cost through Ovshinsky’s invention of a system for mass-producing the cells “roll-to-roll” in a continuous process. While Ovshinsky conceived of this process, it was the job of his talented staff to solve the incredibly challenging engineering problems involved in roll-coating the multi-layered solar panels without cross-contamination. Over nearly three decades, ECD scientists built a series of progressively larger solar cell production machines delivering higher and higher annual power wattage (eventually 30 megawatts), drawing on support first from ARCO and later from Sohio, Sharp, Canon, Sovlux, and Bekaert. ECD’s United Solar division eventually became the leading US producer of thin-film solar panels.
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Silvestroni, Laura, and Diletta Sciti. "Effect of Transition Metal Silicides on Microstructure and Mechanical Properties of Ultra-High Temperature Ceramics." In MAX Phases and Ultra-High Temperature Ceramics for Extreme Environments, 125–79. IGI Global, 2013. http://dx.doi.org/10.4018/978-1-4666-4066-5.ch005.

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The IV and V group transition metals borides, carbides, and nitrides are widely known as ultra-high temperature ceramics (UHTCs), owing to their high melting point above 2500°C. These ceramics possess outstanding physical and engineering properties, such as high hardness and strength, low electrical resistivity and good chemical inertness which make them suitable structural materials for applications under high heat fluxes. Potential applications include aerospace manufacturing; for example sharp leading edge parts on hypersonic atmospheric re-entry vehicles, rocket nozzles, and scramjet components, where operating temperatures can exceed 3000°C. The extremely high melting point and the low self-diffusion coefficient make these ceramics very difficult to sinter to full density: temperatures above 2000°C and the application of pressure are necessary conditions. However these processing parameters lead to coarse microstructures, with mean grain size of the order of 20 µm and trapped porosity, all features which prevent the achievement of the full potential of the thermo-mechanical properties of UHTCs. Several activities have been performed in order to decrease the severity of the processing conditions of UHTCs introducing sintering additives, such as metals, nitrides, carbides or silicides. In general the addition of such secondary phases does decrease the sintering temperature, but some additives have some drawbacks, especially during use at high temperature, owing to their softening and the following loss of integrity of the material. In this chapter, composites based on borides and carbides of Zr, Hf and Ta were produced with addition of MoSi2 or TaSi2. These silicides were selected as sintering aids owing to their high melting point (>2100°C), their ductility above 1000°C and their capability to increase the oxidation resistance. The microstructure of fully dense hot pressed UHTCs containing 15 vol% of MoSi2 or TaSi2, was characterized by x-ray diffraction, scanning, and transmission electron microscopy. Based on microstructural features detected by TEM, thermodynamical calculations, and the available phase diagrams, a densification mechanism for these composites is proposed. The mechanical properties, namely hardness, fracture toughness, Young’s modulus and flexural strength at room and high temperature, were measured and compared to the properties of other ultra-high temperature ceramics produced with other sintering additives. Further, the microstructural findings were used to furnish possible explanations for the excellent high temperature performances of these composites.
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Conference papers on the topic "Sharp leading edges"

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Lofthouse, Andrew, and Iain Boyd. "Nonequilibrium Aerothermodynamics of Sharp-Leading Edges." In 47th AIAA Aerospace Sciences Meeting including The New Horizons Forum and Aerospace Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-1316.

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Walker, Sandra, and Brian Sullivan. "Sharp Refractory Composite Leading Edges on Hypersonic Vehicles." In 12th AIAA International Space Planes and Hypersonic Systems and Technologies. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.2003-6915.

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NAKAMURA, YOSHIAKI, and MICHIRU YASUHARA. "A hypersonic flow in a channel with sharp leading edges." In 20th Fluid Dynamics, Plasma Dynamics and Lasers Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-1841.

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Reuther, James, David Kinney, Stephen Smith, Dean Kontinos, Peter Gage, and David Saunders. "A reusable space vehicle design study exploring sharp leading edges." In 35th AIAA Thermophysics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-2884.

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Steeves, Craig A., Ming Y. He, Lorenzo Valdevit, Scott Kasen, Hossein Haj-Hariri, Haydn N. G. Wadley, and Anthony G. Evans. "Metallic Structural Heat Pipes as Sharp Leading Edges for Mach 7 Vehicles." In ASME 2007 International Mechanical Engineering Congress and Exposition. ASMEDC, 2007. http://dx.doi.org/10.1115/imece2007-42397.

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Sharp leading edges on hypersonic vehicles experience very large heating loads and consequent high temperatures. One strategy for for accommodating these effects is to provide very high effectively thermal conductivity which allows heat to be transferred from the hot leading edge to large cool surfaces for radiation into space. Heat pipes integrated within metallic leading edges provide this function, as well as being easy to manufacture and highly robust compared to other material choices. This paper will examine the feasibility of metallic leading edge heat pipes for hypersonic vehicles in Mach 7 flight. Using temperatures and heat fluxes calculated elsewhere, analytic approximations of the temperature distributions and stresses in a prototypical system are analyzed. The analysis is supplemented and confirmed by finite element calculations. Feasibility of the system is assessed by simple calculations on the operational limits of heat pipes.
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Santos, Wilson. "Flowfield Characteristics of Sharp/Blunt Leading Edges for Hypersonic Waverider Configurations." In 46th AIAA Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-1183.

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JONES, KEVIN, and F. DOUGHERTY. "Computational simulation of flows about hypersonic geometries with sharp leading edges." In Flight Simulation Technologies Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-3065.

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Scatteia, L., M. Balat Pichelin, F. Monteverde, R. Savino, A. Del Vecchio, and S. Cantoni. "Surface Properties and Oxidation Behaviour of Ultra High Temperature Ceramics for Sharp Leading Edges." In 57th International Astronautical Congress. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.iac-06-c2.4.04.

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Calvert, W. John. "An Inviscid-Viscous Method to Model Leading Edge Separation Bubbles." In ASME 1994 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1994. http://dx.doi.org/10.1115/94-gt-247.

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Separation bubbles are likely to occur near the leading edges of sharp-edged blade sections in axial compressors and turbines, particularly when the sections are operated at positive incidence. Typically the flow reattaches a short distance from the leading edge as a turbulent boundary layer, the thickness of which depends on the details of the separation bubble. The overall performance of the blade section can be significantly affected by the thickness of this initial boundary layer — in some cases blade stall is mainly associated with the change in thickness of the layer as blade incidence is increased. A recent experimental study at the Whittle Laboratory, Cambridge demonstrated the importance of the blade leading edge shape on the separation bubble. In the present work, an inviscid-viscous method has been set up to model the experimental data and to provide a way of predicting the performance of this critical region for different leading edge shapes.
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Roghelia, Amit, Pavel V. Chuvakhov, Herbert Olivier, and Ivan Egorov. "Experimental investigation of Görtler vortices in hypersonic ramp flows behind sharp and blunt leading edges." In 47th AIAA Fluid Dynamics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2017. http://dx.doi.org/10.2514/6.2017-3463.

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