標(biāo)題: Titlebook: Drag Reduction by Shock and Boundary Layer Control; Results of the Proje Egon Stanewsky,Jean Délery,Paolo Matteis Conference proceedings 20 [打印本頁(yè)] 作者: Covenant 時(shí)間: 2025-3-21 16:35
書目名稱Drag Reduction by Shock and Boundary Layer Control影響因子(影響力)
書目名稱Drag Reduction by Shock and Boundary Layer Control影響因子(影響力)學(xué)科排名
書目名稱Drag Reduction by Shock and Boundary Layer Control網(wǎng)絡(luò)公開度
書目名稱Drag Reduction by Shock and Boundary Layer Control網(wǎng)絡(luò)公開度學(xué)科排名
書目名稱Drag Reduction by Shock and Boundary Layer Control被引頻次
書目名稱Drag Reduction by Shock and Boundary Layer Control被引頻次學(xué)科排名
書目名稱Drag Reduction by Shock and Boundary Layer Control年度引用
書目名稱Drag Reduction by Shock and Boundary Layer Control年度引用學(xué)科排名
書目名稱Drag Reduction by Shock and Boundary Layer Control讀者反饋
書目名稱Drag Reduction by Shock and Boundary Layer Control讀者反饋學(xué)科排名
作者: SOW 時(shí)間: 2025-3-21 20:27
Vassiliki Avgerinou,Stefanos G. Giakoumatosol on buffet onset..Two airfoils have been considered for the computations: the laminar DRA-2303 and the turbulent RAE-5225. Both airfoils were tested at DERA and hence experimental results were available allowing to make comparisons between the predicted numerical results and those obtained experimentally.作者: infelicitous 時(shí)間: 2025-3-22 03:06
Vassiliki Avgerinou,Stefanos G. Giakoumatosr damping of buffet. The 3D-unsteady code VIS25, developed at ONERA as an extension of the 2D VIS 15 code, has finally been used to study sweep effects on the flow with and without bump in the case of the ADIF sheared wing.作者: Cabinet 時(shí)間: 2025-3-22 06:58 作者: 災(zāi)難 時(shí)間: 2025-3-22 10:04
Hybrid and Active Control of Shock Wave — Turbulent Boundary Layer Interaction and Perforated Plate tension of the transpiration law has been derived which takes into account the effect of tangential stream along a porous plate..Numerical simulations have been extended to a 3-D analysis of the flow in a channel Here, it was found that 3-D effects are responsible for the discrepancy between experiment and 2-D calculations performed earlier.作者: nettle 時(shí)間: 2025-3-22 14:55 作者: nettle 時(shí)間: 2025-3-22 20:35 作者: 討好美人 時(shí)間: 2025-3-22 23:46
An Investigation of Active, Suction, Shock and Boundary Layer Control Techniquesfiguration of Active Suction does not reduce drag, but theoretical parametric studies have revealed a potential control system, which could be examined by a simple modification to the existing system. Hybrid Suction is shown to be in-effective at reducing drag.作者: 同步信息 時(shí)間: 2025-3-23 03:21
Introduction to the Individual Contributions of the work performed by the various members of EUROSHOCK II, written by these members. The contributions, Chapters 11 through 24, are assembled in the order of the four tasks which comprise the research project. The sequence of the individual contributions and the main contents of the research performed are briefly outlined below.作者: 有常識(shí) 時(shí)間: 2025-3-23 07:43 作者: RECUR 時(shí)間: 2025-3-23 12:28 作者: pineal-gland 時(shí)間: 2025-3-23 14:10
1612-2909 n Market is strongly dependent on such factors as time-to-market of a new or derivative aircraft and on its manufacturing costs but also on the achievement of a competitive technological advantage by which an increased market share can be gained. Recognizing this, cooperative research is continuousl作者: Anthropoid 時(shí)間: 2025-3-23 18:44 作者: 處理 時(shí)間: 2025-3-23 23:45 作者: 清真寺 時(shí)間: 2025-3-24 04:52
Conference proceedings 2002-market of a new or derivative aircraft and on its manufacturing costs but also on the achievement of a competitive technological advantage by which an increased market share can be gained. Recognizing this, cooperative research is continuously encouraged and co-financed by the European Union in ord作者: resistant 時(shí)間: 2025-3-24 06:31 作者: nutrients 時(shí)間: 2025-3-24 11:30 作者: parsimony 時(shí)間: 2025-3-24 16:45 作者: Binge-Drinking 時(shí)間: 2025-3-24 19:03
Steady and Unsteady Numerical NS-Calculations for the DRA 2303 Airfoil with and without Bumpe calculations have shown that agreement was achieved in most cases. As far as steady drag calculations are concerned, at least the right tendencies have been predicted, although the absolute values differed from the experimental data.作者: 我不明白 時(shí)間: 2025-3-25 02:50
Euler/Boundary Layer Coupling to Predict Steady and Unsteady Transonic Flows Past an Airfoil with ann of buffet onset is consistent with other methods, but quantitative differences have been found. Results clearly indicate that control devices can be helpful in reducing drag and in delaying buffet onset to higher lift coefficients or Mach numbers.作者: 夾克怕包裹 時(shí)間: 2025-3-25 05:50
Synopsis of the Project EUROSHOCK IImining the design and off-design performance of transonic transport aircraft in the case of a turbulent wing but more so for laminar wings where moderate to strong shock waves may already be present at cruise conditions in order to take full advantage of the potential of laminarization. Based on the作者: 不出名 時(shí)間: 2025-3-25 08:53
Introduction to the Individual Contributionswas, however, a team effort with the individual work adding up to the final product. The Synopsis is therefore followed by a more detailed description of the work performed by the various members of EUROSHOCK II, written by these members. The contributions, Chapters 11 through 24, are assembled in t作者: 洞察力 時(shí)間: 2025-3-25 14:49
Study of Control Devices Applied to a Transonic Shock Wave/Boundary Layer Interactionitions. Several control techniques have been investigated: 1) active control consisting in sucking a part of the boundary layer flow through a slot, 2) hybrid control, which is a combination of a passive control cavity placed underneath the shock region and a suction slot (or cavity) located downstr作者: inclusive 時(shí)間: 2025-3-25 16:40
Hybrid and Active Control of Shock Wave — Turbulent Boundary Layer Interaction and Perforated Plate suction downstream of the passive control cavity is able not only to suppress separation but even to restore the boundary layer to the velocity profile shape present without control. Active control by suction through a single cavity is even more effective. The boundary layer resulting from active co作者: Altitude 時(shí)間: 2025-3-25 23:55 作者: 遭受 時(shí)間: 2025-3-26 01:33 作者: ostrish 時(shí)間: 2025-3-26 06:29
Euler/Boundary Layer Coupling to Predict Steady and Unsteady Transonic Flows Past an Airfoil with anyer interaction in transonic flow for the reduction of both, drag and buffet effects. Applications concerned the effectiveness of suction and of a bump at Mach numbers prior to and beyond buffet onset. Good agreement with experiments has been found for the pressure distributions, while the predictio作者: 偽造 時(shí)間: 2025-3-26 10:43
2D Numerical Investigations of Shock and Boundary Layer Control Techniquesnd airfoils with different devices used to control the shock boundary layer interaction phenomenon..The numerical investigations have been carried out in two phases. In a first step, steady calculations were performed in order to understand how the control devices affect the main flow and to determi作者: Ibd810 時(shí)間: 2025-3-26 14:27
Prediction of Transonic Airfoil/Wing Flow and Buffet with Control Using a Time-accurate Viscous-Invicid interaction codes VIS15 and VIS25 within Task 2 of EUROSHOCK II. The 2D code VIS15 has been used to study the influence of bumps, discrete suction, hybrid control, and passive and active control through perforated walls in the case of different laminar and turbulent airfoils. The time-accurate 2作者: Hearten 時(shí)間: 2025-3-26 20:45 作者: FLING 時(shí)間: 2025-3-26 23:54 作者: FLOUR 時(shí)間: 2025-3-27 02:47
Experimental Investigation of the Transonic Airfoils ADIF and DA LVA-1A and the ADIF Sheared Wing win terms of cruise drag, hence speed and/or fuel consumption, and with respect to the drag-rise and buffet boundaries. An extensive wind tunnel program on airfoils and an infinitely-swept sheared wing was, therefore, carried out investigating the effect of shock and boundary layer control on the impr作者: 舊石器 時(shí)間: 2025-3-27 07:26 作者: 提名的名單 時(shí)間: 2025-3-27 12:01
Assessment of Bump Control and its Application to a Long-range Turbulent-wing Aircrafttrol to an A340-type aircraft wing of existing turbulent design and to determine benefits and penalties of control implementation on the operational aircraft. The control mechanism considered was foremost the contour bump. (Originally, also a new turbulent wing design with integrated bump should hav作者: 1FAWN 時(shí)間: 2025-3-27 17:40
Drag Reduction and Buffet Damping by a Contour Bump Control Device and Regional-jet Application drag in transonic flow and to allow damping of aerodynamic buffet. Evaluations on 2D airfoils have been performed using the ALN Navier-Stokes code. Indications have been obtained that a local, well designed, upper surface deformation (bump) can sensibly reduce airfoil drag in transonic flow in a la作者: Ferritin 時(shí)間: 2025-3-27 18:49 作者: ineptitude 時(shí)間: 2025-3-27 23:41
Drag Reduction by Shock and Boundary Layer Control978-3-540-45856-2Series ISSN 1612-2909 Series E-ISSN 1860-0824 作者: 財(cái)產(chǎn) 時(shí)間: 2025-3-28 06:09
Charles C. J. Carpenter,Richard B. Hornickmining the design and off-design performance of transonic transport aircraft in the case of a turbulent wing but more so for laminar wings where moderate to strong shock waves may already be present at cruise conditions in order to take full advantage of the potential of laminarization. Based on the作者: 切掉 時(shí)間: 2025-3-28 09:27 作者: Engaged 時(shí)間: 2025-3-28 11:04 作者: 文字 時(shí)間: 2025-3-28 16:09 作者: certitude 時(shí)間: 2025-3-28 21:09 作者: 燈絲 時(shí)間: 2025-3-29 01:01
https://doi.org/10.1007/978-1-4419-6630-8airfoil performance (drag reduction and buffet onset) using shock and boundary-layer active control techniques. The numerical flow simulation has been performed using the computational capabilities developed within EUROSHOCK (I) and the results have been validated through comparison with the experim作者: licence 時(shí)間: 2025-3-29 06:57
Sports Economics, Management and Policyyer interaction in transonic flow for the reduction of both, drag and buffet effects. Applications concerned the effectiveness of suction and of a bump at Mach numbers prior to and beyond buffet onset. Good agreement with experiments has been found for the pressure distributions, while the predictio作者: Ossification 時(shí)間: 2025-3-29 07:39 作者: Popcorn 時(shí)間: 2025-3-29 12:03 作者: 過分 時(shí)間: 2025-3-29 18:10
Violence and Aggression in Sporting Contestssteady as well as the unsteady transonic flow about this airfoil with and without a bump. The following work has been carried out and analysed in detail: ① calculations of the steady lift-, drag- and pitching moment distributions for the datum airfoil and the airfoil with bump, ② implementation of n作者: 死貓他燒焦 時(shí)間: 2025-3-29 20:15
Pseudocapillarization and the Aging Liverontrol systems are all ‘a(chǎn)ctive’ in the sense that they utilise suction to remove some of the mass flow within the boundary layer. The systems considered were:.In assessing the potential benefits of these ‘a(chǎn)ctive’ suction systems it is necessary to allow for the internal or ‘pump’ drag to arrive at a作者: VICT 時(shí)間: 2025-3-30 02:50
Alexander Zipprich,Roberto J. Groszmannn terms of cruise drag, hence speed and/or fuel consumption, and with respect to the drag-rise and buffet boundaries. An extensive wind tunnel program on airfoils and an infinitely-swept sheared wing was, therefore, carried out investigating the effect of shock and boundary layer control on the impr作者: Perineum 時(shí)間: 2025-3-30 06:23 作者: 閑蕩 時(shí)間: 2025-3-30 08:58 作者: 女上癮 時(shí)間: 2025-3-30 15:36 作者: 半球 時(shí)間: 2025-3-30 19:42 作者: insular 時(shí)間: 2025-3-30 23:46
https://doi.org/10.1007/978-3-540-45856-2Fluid mechanics; aircraft engines; aircraft wings; boundary layers; flow control; modeling; shock waves; si作者: BRAWL 時(shí)間: 2025-3-31 04:09 作者: fringe 時(shí)間: 2025-3-31 06:08 作者: 補(bǔ)充 時(shí)間: 2025-3-31 09:50 作者: emission 時(shí)間: 2025-3-31 14:53
