Relevant bibliographies by topics / Leading-edge suction

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

Academic literature on the topic 'Leading-edge suction'

Author: Grafiati
Published: 4 June 2021
Last updated: 9 February 2022

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Journal articles on the topic "Leading-edge suction"

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Badran, B., S. McCormick, and I. Gursul. "Control of Leading-Edge Vortices with Suction." Journal of Aircraft 35, no. 1 (January 1998): 163–65. http://dx.doi.org/10.2514/2.2279.

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Wong, P. W. C., M. Maina, and A. M. Cobbin. "Transition and separation control in the leading edge region." Aeronautical Journal 105, no. 1049 (July 2001): 371–78. http://dx.doi.org/10.1017/s0001924000012288.

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Abstract This paper describes an investigation of methods of controlling transition and separation in the leading edge region of military aircraft wings. For wings with the high leading edge sweep relevant to some military aircraft, if attachment line contamination can be prevented then transition is predominantly caused by crossflow instability close to the leading edge. The use of surface suction or cooling for suppressing these instabilities in order to delay transition, has been investigated in a parametric study. The placing of a short suction panel close to the leading edge has been found to be an effective means of controlling instability. Conversely, the level of cooling required to suppress crossflow instability may be too high for practical aircraft applications. The use of suction for preventing laminar separation for pressure distributions with a leading edge suction peak has also been included in the parametric study. The suction quantity required is strongly dependent on the peak height. The suction quantity that can be achieved in practice will limit the maximum peak height that can be attained without laminar separation. An investigation of leading edge stall and control has also been carried out. The analysis suggests that it is important to be able to identify whether the stall is due to laminar bubble bursting or turbulent re-separation, since different methods of controlling the stall may be required.
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Er-El, Joseph, and Zohar Yitzhak. "Experimental examination of the leading-edge suction analogy." Journal of Aircraft 25, no. 3 (March 1988): 195–99. http://dx.doi.org/10.2514/3.45577.

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4

Arnal, D., J. C. Juillen, J. Reneaux, and G. Gasparian. "Effect of wall suction on leading edge contamination." Aerospace Science and Technology 1, no. 8 (December 1997): 505–17. http://dx.doi.org/10.1016/s1270-9638(97)90000-6.

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5

Parmenter, K., and D. Rockwell. "Transient response of leading-edge vortices to localized suction." AIAA Journal 28, no. 6 (June 1990): 1131–33. http://dx.doi.org/10.2514/3.25177.

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6

Deparday, J., and K. Mulleners. "Critical evolution of leading edge suction during dynamic stall." Journal of Physics: Conference Series 1037 (June 2018): 022017. http://dx.doi.org/10.1088/1742-6596/1037/2/022017.

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7

Hardy, B. C., and S. P. Fiddes. "Prediction of vortex lift of non-planar wings by the leading-edge suction analogy." Aeronautical Journal 92, no. 914 (April 1988): 154–64. http://dx.doi.org/10.1017/s0001924000025562.

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SummaryA three-dimensional panel method has been used to calculate edge-suction forces for thin sharp-edged wings in incompressible flow. The suction forces have been used to estimate the vortex lift on the wings by means of the leading-edge suction analogy due to Polhamus.The results for planar wings are in acceptable agreement with other methods based on the suction analogy. A limited comparison with results from experiments for non-planar wings revealed good prediction of lift and drag increments associated with the deflection of leading and trailing edge flaps for ‘conventional’ wings of high sweep, but only moderate agreement for a grossly non-planar configuration.
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Wang, Chao, Ying Xiong, Guo Liang Wang, and Hai Peng Guo. "Prediction of Hydrodynamic Performance of Hydrofoil with Suction and Jet Equipment." Applied Mechanics and Materials 444-445 (October 2013): 432–36. http://dx.doi.org/10.4028/www.scientific.net/amm.444-445.432.

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In order to improve the hydrodynamic performance of the hydrofoil, one new foil is brought forward which has slits near the leading edge and the trailing edge. In this article, the NACA0012 foil whose performance was calculated by CFD method was chose as a study object. And the validity of the CFD method was proved by contrasting the calculation results with the experiments. Through calculating and analyzing the hydrodynamic performance of the new hydrofoil that has suction inlet and jet outlet in the leading edge and the trailing edge respectively, the result shows that such performance of suction-jet hydrofoil has advantages of both suction hydrofoil and water-jet hydrofoil.
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Li, Shao Hua, Li Mei Du, Wen Hua Dong, and Ling Zhang. "A Numerical Study on the Characteristics of How Heat and Cooling Transfer on the Leading Edge of a Film-Cooling Blade." Advanced Materials Research 383-390 (November 2011): 3963–68. http://dx.doi.org/10.4028/www.scientific.net/amr.383-390.3963.

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In this paper, a numerical simulation was performed to investigate heat transferring characteristics on the leading edge of a blade with three rows of holes of film-cooling using Realizable k- model. Three rows of holes were located on the suction side leading edge stagnation line and the pressure surface. The difference of the cooling efficiency and the heat transfer of the three rows of holes on the suction side and pressure side were analyzed; the heat transfer and film cooling effectiveness distribution in the region of leading edge are expounded under different momentum rations.The results show that under the same condition, the cooling effectiveness on the pressure side is more obvious than the suction side, but the heat transfer is better on the suction side than the pressure side. The stronger momentum rations are more effective cooling than the heat transfer system.
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Hobson, Garth V., Bryce E. Wakefield, and William B. Roberts. "Turbulence Amplification with Incidence at the Leading Edge of a Compressor Cascade." International Journal of Rotating Machinery 5, no. 2 (1999): 89–98. http://dx.doi.org/10.1155/s1023621x99000081.

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Detailed measurements, with a two-component laser-Doppler velocimeter and a thermal anemometer were made near the suction surface leading edge of controlled-diffusion airfoils in cascade. The Reynolds number was near 700,000, Mach number equal to 0.25, and freestream turbulence was at 1.5% ahead of the cascade.It was found that there was a localized region of high turbulence near the suction surface leading edge at high incidence. This turbulence amplification is thought to be due to the interaction of the free-shear layer with the freestream inlet turbulence. The presence of the local high turbulence affects the development of the short laminar separation bubble that forms very near the suction side leading edge of these blades. Calculations indicate that the local high levels of turbulence can cause rapid transition in the laminar bubble allowing it to reattach as a short “non-burst” type.The high turbulence, which can reach point values greater than 25% at high incidence, is the reason that leading edge laminar separation bubbles can reattach in the high pressure gradient regions near the leading edge. Two variations for inlet turbulence intensity were measured for this cascade. The first is the variation ofmaximum inlet turbulence with respect to inlet-flow angle; and the second is the variation of leading edge turbulence with respect to upstream distance from the leading edge of the blades.
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Dissertations / Theses on the topic "Leading-edge suction"

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"The Effect of Leading-Edge Geometry on the Induced Drag of a Finite Wing." Master's thesis, 2019. http://hdl.handle.net/2286/R.I.53549.

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abstract: This study identifies the influence that leading-edge shape has on the aerodynamic characteristics of a wing using surface far-field and near-field analysis. It examines if a wake survey is the appropriate means for measuring profile drag and induced drag. The paper unveils the differences between sharp leading-edge and blunt leading-edge wings with the tools of pressure loop, chordwise pressure distribution, span load plots and with wake integral computations. The analysis was performed using Computational Fluid Dynamics (CFD), vortex lattice potential flow code (VORLAX), and a few wind-tunnels runs to acquire data for comparison. This study found that sharp leading-edge wings have less leading-edge suction and higher drag than blunt leading-edge wings. The blunt leading-edge wings have less drag because the normal vector of the surface in the front section of the airfoil develops forces at opposed skin friction. The shape of the leading edge, in conjunction with the effect of viscosity, slightly alter the span load; both the magnitude of the lift and the transverse distribution. Another goal in this study is to verify the veracity of wake survey theory; the two different leading-edge shapes reveals the shortcoming of Mclean’s equation which is only applicable to blunt leading-edge wings.
Dissertation/Thesis
Masters Thesis Aerospace Engineering 2019
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Books on the topic "Leading-edge suction"

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A, Campbell Bryan, and Langley Research Center, eds. Subsonic investigation of a leading-edge boundary layer cont[r]ol suction system on a high-speed civil transport configuration. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1999.

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A, Campbell Bryan, and Langley Research Center, eds. Subsonic investigation of a leading-edge boundary layer cont[r]ol suction system on a high-speed civil transport configuration. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1999.

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Book chapters on the topic "Leading-edge suction"

1

Fuchiwaki, Masaki. "Dynamic Behavior of Leading Edge Vortex and Vorticity on Suction Surface of a Heaving Elastic Airfoil." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 237–50. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-55594-8_22.

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2

Juillen, J. C., and D. Arnal. "Experimental Study of Boundary Layer Suction Effects on Leading Edge Contamination along the Attachment Line of a Swept Wing." In Laminar-Turbulent Transition, 173–80. Berlin, Heidelberg: Springer Berlin Heidelberg, 1995. http://dx.doi.org/10.1007/978-3-642-79765-1_20.

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Conference papers on the topic "Leading-edge suction"

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Ramesh, Kiran Kumar, Ashok Gopalarathnam, Kenneth Granlund, Michael Ol, and Jack Edwards. "Theoretical Modeling of Leading Edge Vortices Using the Leading Edge Suction Parameter." In 30th AIAA Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-3027.

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Ng, T., and Russell Osborn. "Control of leading edge separation using discrete suction." In 38th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-651.

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Schulten, Johan. "Unsteady leading edge suction effects on rotor-stator interaction noise." In 5th AIAA/CEAS Aeroacoustics Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1999. http://dx.doi.org/10.2514/6.1999-1951.

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Maines, Brant, Brian Moeller, and Othon Rediniotis. "The effects of leading edge suction on delta wing vortex breakdown." In 37th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1999. http://dx.doi.org/10.2514/6.1999-128.

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Li, Wei-Lin, and Eli Livne. "Design oriented leading edge suction force prediction for supersonic lifting surfaces." In 6th Symposium on Multidisciplinary Analysis and Optimization. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1996. http://dx.doi.org/10.2514/6.1996-4171.

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6

Farhat, Mohamed, Faic¸al Gennoun, and Franc¸ois Avellan. "The Leading Edge Cavitation Dynamics." In ASME 2002 Joint U.S.-European Fluids Engineering Division Conference. ASMEDC, 2002. http://dx.doi.org/10.1115/fedsm2002-31000.

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In the present paper, we present an experimental investigation of the onset and detachment of a leading edge cavitation over a 2-D and 3-D hydrofoils. An insight of the flow field in the vicinity of the main cavity detachment is reached with the help of a miniature sensor fitted in a NACA009 hydrofoil suction side close to the leading edge stagnation point. Owing to theses experiments, we have demonstrated how the water may withstand negative pressure as low as −0.8 bar without any visible cavitation. As soon as the leading edge cavitation takes place, the pressure upstream to the cavity detachment rises significantly but remains negative while the measured pressure in the cavity is almost equal to the vapor pressure. This result confirms the assumption already stated by former studies according to which the liquid is in tension just upstream to the detachment point. Furthermore, flow visualization clearly shows that a well developed leading edge cavitation turns into bubble cavitation in a continuous way when the surrounding pressure is gradually increased. Owing to those results, we have introduced a physical model of the cavitation detachment in which, no laminar separation of the boundary layer is required to ensure its mechanical equilibrium as already stated by former studies. The nuclei in the vicinity of the blade surface explode as they cross the liquid-vapor interface, which is not a material surface. The main cavity is thus continuously fed with exploding bubbles at its detachment location. The negative pressure measured upstream to the cavity detachment may thus be explained by the dynamic delay of exploding nuclei due to inertia.
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Ardey, Sabine, Stefan Wolff, and Leonhard Fottner. "Turbulence Structures of Leading Edge Film Cooling Jets." In ASME Turbo Expo 2000: Power for Land, Sea, and Air. American Society of Mechanical Engineers, 2000. http://dx.doi.org/10.1115/2000-gt-0255.

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For a better understanding of the turbulence structures attached to film cooling jets, mean flow velocities and turbulent fluctuations were measured by means of 3D hot wire anemometry in the injection zone of a linear, large scale, high pressure turbine cascade with leading edge film cooling. Near the stagnation point, the blades are equipped with one row of film cooling holes each on the suction and pressure side. Two basically different coolant jet situations are compared: On the suction side the jet features the ordinary kidney vortex. On the pressure side, the jet separates completely from the blade surface since it is located above a large recirculation zone created by a locally adverse pressure gradient and a flow separation near the pressure side injection. The measured Reynolds stresses were analyzed with regard to turbulence production and diffusion. The Bousinesque Hypothesis was tested and could not be confirmed. It was found that the turbulence is highly anisotropic. In addition to the brief description of the experimental set up and the acquired data, given in this paper, the complete information are published as a test case (Ardey and Fottner, 1998) that is directly accessible via internet at: http://www.unibw-muenchen.de/campus/LRT12/welcome.html
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Henderson, Alan D., Gregory J. Walker, and Jeremy D. Hughes. "Unsteady Transition Phenomena at a Compressor Blade Leading Edge." In ASME Turbo Expo 2006: Power for Land, Sea, and Air. ASMEDC, 2006. http://dx.doi.org/10.1115/gt2006-90641.

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Wake-induced laminar-turbulent transition is studied at the leading edge of a C4-section compressor stator blade in a 1.5-stage axial compressor. Surface hot-film sensor observations are interpreted with the aid of numerical solutions from UNSFLO, a quasi three-dimensional viscous-inviscid flow solver. The passage of a rotor wake, with its associated negative jet, over the stator leading edge is observed to have a destabilizing effect on the suction surface boundary layer. This leads to transition closer to the stator leading edge than would have occurred under steady flow conditions. The strength of this phenomenon is influenced by the rotor-stator axial gap and the variability of individual rotor wake disturbances. A variety of transition phenomena are observed near the leading edge in the wake path. Wave packets characteristic of Tollmien–Schlichting waves are observed to amplify and break down into turbulent spots. Disturbances characteristic of the streaky structures occurring in bypass transition are also seen. Examination of suction surface disturbance and wake-induced transitional strip trajectories points to the leading edge as the principal receptivity site for suction surface transition phenomena at design loading conditions. This contrasts markedly with the pressure surface behavior, where transition at design conditions occurs remote from leading edge flow perturbations associated with wake chopping. Here the local receptivity of the boundary layer to the wake passing disturbance and turbulent wake fluid discharging onto the blade surface may be of greater importance.
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Narsipur, Shreyas, Pranav Hosangadi, Ashok Gopalarathnam, and Jack R. Edwards. "Variation of Leading-Edge Suction at Stall for Steady and Unsteady Airfoil Motions." In 54th AIAA Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2016. http://dx.doi.org/10.2514/6.2016-1354.

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10

Alrefai, Mah'd, and Mukund Acharya. "Controlled leading-edge suction for the management of unsteady separation over pitching airfoils." In Fluid Dynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1995. http://dx.doi.org/10.2514/6.1995-2188.

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Reports on the topic "Leading-edge suction"

1

Gursul, Ismet. Control of Leading-Edge Vortices With Suction. Fort Belvoir, VA: Defense Technical Information Center, October 1996. http://dx.doi.org/10.21236/ada320167.

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