Numerical Investigation of Tangential Blowing at the Rudder of a Vertical Tailplane Airfoil

Kröhnert, Anna

doi:10.2514/6.2014-2143

Cited by 7 publications

(4 citation statements)

References 8 publications

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“…Numerical work preceding the studies presented herein focused on the sensitivities of different active flow control parameters using a 2D VTP airfoil [11]. The current study extends this to 3D.…”

Section: Introductionmentioning

confidence: 86%

“…The slot height h Slot is 0.0006 of the chord length leading to a relatively thin slot. This height was also used for the preceding 2D investigations [11]. A part of the slot is modelled for numerical reasons [12].…”

Section: Geometry Setupmentioning

confidence: 99%

“…Some aspects of mesh dependence were studied in a preliminary investigation described in [11] for a 2D case and were transferred to the current 2.5D mesh. The farfield extends 100 times the VTP chord length in x-and y-direction.…”

Section: Mesh Generationmentioning

confidence: 99%

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Numerical investigation of slot variations on the efficiency of tangential blowing at a vertical tailplane with infinite span

Gebhardt

Kirz

2018

CEAS Aeronaut J

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On a swept vertical tailplane with infinite span tangential blowing over the shoulder of a deflected rudder is applied. For large rudder deflection angles the flow on the rudder is separated without blowing. A numerical study is conducted with the aim to increase the side force coefficient. This could for example be required during takeoff if the engine on one side fails, necessitating the compensation of a large yawing moment. If this criterion is critical for the sizing of the vertical tailplane, active flow control like tangential blowing could help to reduce the size of the vertical tailplane and thus save weight and fuel. With a continuous slot it is demonstrated that the separation on the rudder can be reduced or avoided. It is shown that by using discrete slots this can be achieved with a smaller momentum coefficient. To analyze the effects of the discrete slots and their jets on each other and their effectivity with regard to the gain in side force coefficient a parameter study is conducted. The number of slots as well as the size of the slots in spanwise direction is varied and the impact of jet velocity changes is also studied. In comparing the results for a constant increase in side force and constant slot size in spanwise direction the configuration with the smaller number of slots but a higher jet velocity proved to be the most effective one.

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Section: Introductionmentioning

confidence: 86%

Section: Geometry Setupmentioning

confidence: 99%

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Numerical investigation of slot variations on the efficiency of tangential blowing at a vertical tailplane with infinite span

Gebhardt

Kirz

2018

CEAS Aeronaut J

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“…They concluded that the actuators act as fluidic boundary layer fences and that a limited number of actuators (two in this case) with a C μ of 1% were able to reach the same lift coefficient than twenty nine actuators with a C μ of 2%. Like Pack Melton et al [7]- [11], Krӧhnert [31] investigated numerically a simplified two-dimensional configuration. A lift increment of 0.8 was reached with a steady blowing slot with a C μ of 2.5%.…”

Section: Introductionmentioning

confidence: 99%

Performance Enhancement of a Vertical Tail Model with Sweeping Jets

2020

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Active flow control to delay the flow separation on the rudder of two different models has been investigated in the ONERA L1 wind tunnel. The first model was used as a simplified test case and consisted in a flat plate with a rudder. Different types of actuation were investigated: continuous/pulsed blowing through slots, continuous blowing through segmented slots and sweeping jets. The lift increments of these different types of actuation were compared not only in terms of mass flow rate but also in terms of momentum and power coefficients. Active flow control by sweeping jets was selected to be tested on the second model which is a scale 1:2 vertical tail model of a generic business jet. Side force increments up to 80% were achieved with a 2% value of C μ coefficient. Side force increments of 50% were also reached with a lower C μ value of 0.5%. These side force increments could lead to a reduction of vertical tail plane wetted area and weight and consequently to a reduction of drag cruise and fuel consumption.

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Numerical Investigation of Unsteady Tangential Blowing at the Rudder of a Vertical Tailplane Airfoil

Kröhnert

2016

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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This volume contains the papers presented at the 19th DGLR/STAB-Symposium held in Munich, Germany, 4-5 November 2014 and organized by the Institute of Aerodynamics and Fluid Mechanics of the Technische Universität München. STAB is the German Aerospace Aerodynamics Association, founded towards the end of the 1970s and DGLR is the German Society for Aeronautics and Astronautics (Deutsche Gesellschaft für Luft-und Raumfahrt-Lilienthal Oberth e.V.). The mission of STAB is to foster development and acceptance of the disciplines "Aerodynamics and Fluid Mechnics" in Germany. One of its general guidelines is to concentrate resources and know-how in the involved institutions and to avoid duplication in research work as much as possible. Nowadays, this is more necessary than ever. The experience made in the past makes it easier now to obtain new knowledge for solving today's and tomorrow's problems. STAB unites German scientists and engineers from universities, research establishments and industry doing research and project work in numerical and experimental fluid mechanics and aerodynamics for aerospace, ground transportation and other applications. This has always been the basis of numerous common research activities sponsored by different funding agencies. Since 1986 the symposium has taken place at different locations in Germany every 2 years. In between, STAB workshops regularly take place at the DLR in Göttingen. The changing meeting places were established as focal points in Germany's Aerospace Fluid Mechanics Community for a continuous exchange of scientific results and their discussion. Moreover, they are a forum where new research activities can be presented, often resulting in new, commonly organized research and technology projects. It is the tenth time that the contributions to the symposium are published after being subjected to a peer review. The material highlights the key items of integrated research and development based on fruitful collaboration of industry, research establishments and universities. The research areas include airplane and ground vehicle aerodynamics, multidisciplinary optimization and new configurations, turbulence research and modelling, laminar flow control and transition, rotorcraft v

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Numerical Investigation of Tangential Blowing at the Rudder of a Vertical Tailplane Airfoil

Cited by 7 publications

References 8 publications

Numerical investigation of slot variations on the efficiency of tangential blowing at a vertical tailplane with infinite span

Numerical investigation of slot variations on the efficiency of tangential blowing at a vertical tailplane with infinite span

Performance Enhancement of a Vertical Tail Model with Sweeping Jets

Numerical Investigation of Unsteady Tangential Blowing at the Rudder of a Vertical Tailplane Airfoil

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