| Autor(en) | Neuert, Nora Linde Muriel | Dinkler, Dieter |
|---|---|
| Titel | Aeroelastic behaviour of a parameterised circulation-controlled wing |
| Herausgeber | CEAS Aeronautical Journal |
| Erscheinungsjahr | 2019 |
| Abstract | The aeroelastic behaviour of the wing of a short take-off and landing aircraft using the Coanda effect depends on its properties and shape. An existing reduced-order model is parameterised for detailed investigations. On the one hand, varying mass due to tank level and varying overall stiffness is implemented in the reduced-order model. The influence of the mass change on the aeroelastic behaviour is reflected in the stability maps. On the other hand, two-dimensional steady and unsteady aerodynamics of different nose shapes are investigated with detailed computational fluid simulations and included in the reduced-order model. The dependence on the profile shape and the frequency is described. Their influence on the aeroelastic behaviour is reflected by the stability maps as well. |
| Autor(en) | Sommerwerk, Kay | Michels, Benedikt | Haupt, Matthias C. | Horst, Peter |
|---|---|
| Titel | Influence of engine modeling on structural sizing and approach aerodynamics of a circulation controlled wing |
| Herausgeber | CEAS Aeronaut J, Volume 9, Issue 1, Pages 219-233, Springer, Vienna |
| Erscheinungsjahr | 2018 |
| Abstract | Extended configurations of a short take-off and landing aircraft under investigation at the Coordinated Research Centre SFB 880 include a morphing droop nose and a tractor propeller engine. The short take-off and landing capabilities are achieved by circulation control via a high velocity jet over the flap leading edges utilizing the Coanda effect. The effect of the engine integration in combination with the blown flaps on the wing sizing, aerodynamic performance, and static wing deformation are of large interest. High-detail structural wing models are sized with a fully stressed approach using a partitioned fluid-structure interaction process. The aerodynamic part is covered by highly detailed computational fluid simulations. The effect of modeling the engine on the global and local aerodynamics for different levels of circulation control has a large impact. In addition, a change in flow separation behavior due to the engine effects is observed. The wing mass is only slightly increased by the detailed engine aerodynamics and the separation behavior changes slightly for the elastic wing. These findings show that the modeling of the engine will lead to a different stall behavior and allow for a higher lift, while the influence on the wing structure and aeroelasticity are very small. |
| Autor(en) | Horst, Peter | Sommerwerk, Kay | Neuert, Nora | Krukow, Ian | Keller, Dennis | Diekmann, Jobst | Rang, Joachim | Görtz, Stefan | Krukow, Ian |
|---|---|
| Titel | Flight Dynamics Investigation of an Active High-Lift Aircraft |
| Herausgeber | 35th AIAA Applied Aerodynamics Conference, AIAA AVIATION Forum, Denver, Colorado, 2017 |
| Erscheinungsjahr | 2017 |
| Abstract | The increasing air traffic requires improvements in aircraft design concerning fuel efficiency, noise re- duction, and short take-off and landing (STOL) capabilities. The Sonderforschungsbereich (Coordinated Research Centre) SFB 880 investigates an aircraft with STOL capabilities. The aircraft uses high-pressure air blown through a slot in front of the high lift devices for circulation control. This jet interacts with the boundary layer of the oncoming flow, thus introducing momentum. The increased momentum allows the flow to bend around the flap leading edge due to the Coanda effect. This attached flow, even at very high flap angles of around 65° , results in higher lift coefficients. Consequently, lower approach speeds and shorter runway distances become possible. It is obvious that such aircraft exhibit some unusual characteristics. This paper summarizes some highly interactive results which all end up in a versatile Flight Dynamics model, which allows to investigate the behavior of such aircraft. |
| Autor(en) | Sommerwerk, Kay | Krukow, Ian | Haupt, Matthias | Dinkler, Dieter |
|---|---|
| Titel | Strukturentwurf und Aeroelastik von Flügeln mit aktiver Zirkulationskontrolle |
| Herausgeber | Ingenieurspiegel 10, no. 1, pp 3-5, 2017. |
| Erscheinungsjahr | 2017 |
| Abstract | In der zivilen Luftfahrt steigt der Bedarf nach Flugreisen weiterhin ungebremst. Die prognostizierte Nachfrage kann durch die aktuell nutzbare Infrastruktur nicht bewältigt werden und ein Aus- oder Neubau dieser Flughäfen ist mit großen gesellschaftlichen und politischen Hindernissen verbunden. Ein Lösungsansatz ist die Nutzung neuer Verkehrsmittel, die von der vorhandenen aber bislang kaum genutzten Infrastruktur profitieren können, namentlich den Kleinflughäfen mit für gängige Verkehrsflugzeuge zu kurzen Bahnlängen. Zur Nutzung dieser Flughafen werden Flugzeuge mit ausreichend hohen Kapazitäten benötigt, die die Fähigkeit besitzen, dort starten und landen zu können, dabei für wohngebietsnahe Lagen drastisch verringerten Fluglärm hervorrufen und möglichst wenig Kraftstoff verbrauchen. Dieses Konzept ermöglicht effiziente Punkt-zu-Punkt-Verbindungen, ohne das Erfordernis große Drehkreuzflughäfen anfliegen zu müssen. |
| Autor(en) | Sommerwerk, Kay | Woidt, Malte | Haupt, Matthias | Horst, Peter |
|---|---|
| Titel | Reissner–Mindlin shell implementation and energy conserving isogeometric multi-patch coupling |
| Herausgeber | International Journal for Numerical Methods in Engineering, Vol. 109, Nr. 7, S. 982–1012, (2017) |
| Erscheinungsjahr | 2017 |
| Abstract | A shear-flexible isogeometric Reissner–Mindlin shell formulation using non-uniform rational B-splines basis functions is introduced, which is used for the demonstration of a coupling approach for multiple non-conforming patches. The six degrees of freedom formulation uses the exact surface normal vectors and curvature. The shell formulation is implemented in an isogeometric analysis framework for computation of structures composed of multiple geometric entities. To enable local model refinement as well as non-matching domains coupling, a conservative multi-patch approach using Lagrange multipliers for structured non-uniform rational B-splines patches is presented. Here, an additional border frame mesh is used to couple geometries during structural analyses. This frame interface approach avoids the problem of excessive con- straints when multiple patches are coupled at one point. First, the shell formulation is verified with several reference cases. Then the influence of the frame interface discretization and frame penalty stiffness on the smoothness of the results is investigated. The effects of the perturbed Lagrangian method in combination with the frame interface approach is shown. In addition, results of models with T-joint interface connections and perpendicular stiffener patches are presented. |
| Autor(en) | Sommerwerk, Kay | Haupt, Matthias |
|---|---|
| Titel | Hochauftrieb künftiger Verkehrsflugzeuge – Strukturentwurf und Aeroelastik: Aeroelastische Analysen von Flügeln mit aktiver Zirkulationskontrolle |
| Herausgeber | HLRN Informationen, 19, 2-4 |
| Erscheinungsjahr | 2016 |
| Abstract | Im Rahmen des Sonderforschungsbereichs (SFB) 880 „Grundlagen des Hochauftriebs künftiger Verkehrsflugzeuge“ werden Forschungen zum effizienten Hochauftrieb, den Effekten auf die Aeroakustik sowie der Flugdynamik durchgeführt. Als Grundlage der Forschung und der Technologiebewertung werden die verfolgten Ansätze und Ideen an einem potentiellen Flugzeug geprüft. Im Rahmen des SFB 880, Teilprojekt „Strukturentwurf und Aeroelastik“ werden die wesentlichen Phänomene des aeroelastischen Verhaltens analysiert und Entwurfskonzepte entwickelt. Es gilt sowohl das globale Trag- und Schwingungsverhalten des Tragflügels einschließlich der Phänomene der Zirkulations- und Ruderumkehr, des Low-Speed-Flatterns und der Torsionsdivergenz, als auch das lokale Verhalten – Deformationen der Coandă-Klappen und des Ausblasespaltes – zu untersuchen. |
| Autor(en) | Sommerwerk, Kay | Krukow, Ian | Haupt, Matthias | Dinkler, Dieter |
|---|---|
| Titel | Investigation of Aeroelastic Effects of a Circulation Controlled Wing |
| Herausgeber | AIAA Journal of Aircraft, Vol. 53, No. 6 (2016) |
| Erscheinungsjahr | 2016 |
| Abstract | The aeroelastic behavior of the wing of a 100-passenger aircraft under investigation in the Coordinated Research Center SFB 880 is studied. A compressed air jet upstream of the high-lift devices called the Coandă jet enables boundary layer control with delayed flow separation and consequently high lift. Aeroelastic instabilities caused by boundary layer control systems are critical to the aircraft performance. The understanding of cause and effect of these instabilities is of great importance. For analyses, a multilevel approach is pursued using full-scale three-dimensional models and reduced-order models. Both model types use fluid-structure interaction techniques. The full-scale models are used to generate a sized wing structure with realistic mass and stiffness distributions using computational fluid dynamics loads of cruise and landing configuration load cases. A reduced-order model is derived by modal reduction for computationally efficient investigations of multiple flight states. To study local aeroelastic effects and to develop three- dimensional corrections for the reduced-order model, full-scale three-dimensional coupled fluid-structure analyses are investigated. The results show that especially the dynamic behavior of wings with active circulation control may differ significantly from that of conventional wings due to the different aerodynamic behavior caused by the Coandă jet. |
| Autor(en) | Sommerwerk, Kay | Michels, Benedikt | Haupt, Matthias | Horst, Peter |
|---|---|
| Titel | INVESTIGATION OF ENGINE EFFECTS ON STRUCTURAL SIZING AND STATIC AEROELASTIC SENSITIVITIES OF A CIRCULATION CONTROLLED WING |
| Herausgeber | 65. Deutscher Luft- und Raumfahrtkongress 2016, 13.-15. September 2016, Braunschweig |
| Erscheinungsjahr | 2016 |
| Abstract | Extended configurations of a short take-off and landing aircraft under investigation at the Coordinated Research Centre SFB 880 include a morphing droop nose and a tractor propeller engine. The STOL capabilities are achieved by circulation control via a high velocity jet over the flap leading edges utilizing the Coanda effect. High-detail structural wing models are sized with a fully stressed approach using a partitioned fluid-structure interaction process. The aerodynamic part is covered by highly detailed computational fluid simulations. The effect of the engine integration on the wing mass is small but noteworthy. An aerodynamic performance assessment is conducted for the rigid and flexible wing. The influences of the model extension on the global and local aerodynamic coefficients are presented and their significance is discussed. |
| Autor(en) | Sommerwerk, Kay | Michels, Benedikt | Lindhorst, Klemens | Haupt, Matthias | Horst, Peter |
|---|---|
| Titel | Application of efficient surrogate modeling to aeroelastic analyses of an aircraft wing |
| Herausgeber | Aerospace Science and Technology 55 (2016) 314–323 |
| Erscheinungsjahr | 2016 |
| Abstract | A nonlinear, transient surrogate model is constructed to replace the computational fluid dynamics solver within the aeroelastic analysis of a detailed aircraft wing with variable fuel tank levels during cruise flight. This surrogate model allows high-fidelity analyses at a fraction of the original computational cost with satisfactory accuracy. During the model construction a parameter reduction via proper orthogonal decomposition is combined with a radial basis function artificial network for system identification and nonlinear effects. Transient forced motion computational fluid dynamics analyses based solely on the structural dynamic behavior of the detailed wing model are used as training inputs. To assess the accuracy of the approach the reduced-order model results are compared with high-fidelity full-scale aeroelastic computations. A small local reduction in accuracy can be seen for highly nonlinear effects like dynamic shock movements. However, variations in tank fill level or angle of attack show sufficient agreement of the model with the full-scale analyses. An interpolation of an intermediary angle of attack shows higher errors due to large changes in aerodynamic phenomena between the sample points. |
| Autor(en) | Woidt, Malte | Sommerwerk, Kay | Haupt, Matthias | Horst, Peter |
|---|---|
| Titel | MODELLING STIFFENED LIGHTWEIGHT STRUCTURES WITH ISOGEOMETRIC ANALYSIS VIA MORTAR METHODS |
| Herausgeber | ECCOMAS Congress 2016, VII European Congress on Computational Methods in Applied Sciences and Engineering, Crete Island, Greece, 5–10 June 2016 |
| Erscheinungsjahr | 2016 |
| Abstract | A method to model stiffened panels with NURBS-based isogeometric analysis is presented. Stiffeners and panel are modeled as separate patches and coupled by Mortar methods. The stiffeners and panel meshes can be non-conforming. Therefore modeling of the geometry is simple even with the NURB’s limitation to structured meshes. The feasibility of the method is shown for static and modal analyses. The method is validated against results obtained from standard finite element approaches with conforming meshes for a panel with one stiffener and a panel with multiple stiffeners. For all cases good accordance to the FEM results is observed with a difference of less than 1%. |
| Autor(en) | Dinkler, Dieter | Krukow, Ian |
|---|---|
| Titel | Flutter of circulation-controlled wings |
| Herausgeber | CEAS Aeronaut J, Volume 6, Issue 4, Pages 589-598, Springer, Vienna |
| Erscheinungsjahr | 2015 |
| Abstract | The application of active circulation control gives rise to a substantial increase in lift compared to conventional wings. Initial studies of the aeroelastic behaviour of a circulation-controlled wing have shown additional instabilities due to the active circulation control. Besides the heave flutter phenomenon, further investigation also reveals a destabilising effect of the aerodynamic derivatives related to pitch, which is peculiar to circulation- controlled wings. The goal of the present paper is to investigate these phenomena in detail. |
| Autor(en) | Krukow, Ian | Neuert, Nora | Dinkler, Dieter |
|---|---|
| Titel | Dynamic instabilities of circulation controlled aerofoils |
| Herausgeber | IFASD 2015, St. Petersburg, Russland |
| Erscheinungsjahr | 2015 |
| Abstract | The continuously rising volume of air traffic demands for a correspondingly rising capacity of airports. One possible scenario is the extended use of small, existing airports for point-to-point connections. However, in order to use the shorter runways, the high-lift systems have to be improved significantly. This can be achieved by active circulation control making use of the Coand˘a effect. Though subject to research for several decades, there are still a number of issues to consider in order to make it work for a commercial aircraft. Investigating the aeroelastic behaviour is essential for stability issues. It turns out that the application of active circulation control leads to two additional flutter phenomena, which do not occur with conventional aircraft. Both of them are single degree of freedom flutter – related to heave and pitch motion, respectively – occurring at low velocities as in landing approach. |
| Autor(en) | Krukow, Ian | Dinkler, Dieter |
|---|---|
| Titel | A Reduced-Order Model for the Investigation of the Aeroelasticity of Circulation Controlled Wings |
| Herausgeber | CEAS Aeronautical Journal (2014) 5:145-156 |
| Erscheinungsjahr | 2014 |
| Abstract | The application of active circulation control allows shortening of runways which can be significant in particular cases. The goal of the present paper is to study the influence of the circulation control on the aeroelastic behaviour of wings. For numerical analyses a simplified computational model is presented, which allows for systematic parameter variations. The model is based on model reduction using modal analysis, so that an efficient performance of numerical studies is possible as well as the integration of the aeroelasticity into a flight dynamics model. |
| Autor(en) | Sommerwerk, Kay | Haupt, Matthias |
|---|---|
| Titel | Design analysis and sizing of a circulation controlledCFRP wing with Coanda flaps via CFD-CSMcoupling |
| Herausgeber | CEAS Aeronautical Journal, Vol. 5, No. 1, 2014, pp 95-108 |
| Erscheinungsjahr | 2014 |
| Abstract | Preliminary design tools are essential during aircraft design to make conclusions about an aircraft's performance. Generally this process employs methods of low and medium fidelity to create comparatively fast results for a high number of parameter variations. High fidelity methods are needed to verify theses results and to consider components in more detail. A 100 PAX commercial aircraft with short take-off and landing capabilities of 800 meters with circulation controlled high lift devices is under investigation at the Collaborative Research Centre SFB 880. In this paper, a global wing analysis with a high detail model is conducted and the results are compared with results attained with a preliminary aircraft design tool. Several detailed designs for the air feed system integration are proposed and examined regarding weight and stiffness characteristics on a representative high lift device section model. Fluid-structure coupling is employed during all analyses to transfer aerodynamic loads and structural displacements. The aeroelastic impact of the slot stiffness on the Coanda effect during landing is then quantified. The attained aerodynamic performance results and structural characteristics of each configuration are compared and the advantages are discussed. |
| Autor(en) | Horst, Peter | Keller, Dennis | Diekmann, Jobst Henning | Krukow, Ian | Sommerwerk, Kay |
|---|---|
| Titel | SFB880: Flight Dynamics |
| Herausgeber | Deutscher Luft- und Raumfahrtkongress, Stuttgart, 2013 |
| Erscheinungsjahr | 2013 |
| Abstract | The paper summarizes approaches and first results on flight dynamics of the Collaborative Research Centre SFB 880 - "Fundamentals of High Lift for Future Commercial Aircraft" - , i.e. high fidelity solutions of dynamics in aerodynamics, aeroelasticity and flight control. |
| Autor(en) | Krukow, Ian | Dinkler, Dieter |
|---|---|
| Titel | A reduced-order model for aeroelastic studies on airfoils with active high-lift devices |
| Herausgeber | International Forum on Aeroelasticity and Structural Dynamics, Bristol, UK |
| Erscheinungsjahr | 2013 |
| Abstract | The application of circulation control allows shortening of runways which can be significant in particular cases. To study its influence on the aeroelastic behaviour of the airfoil, a simplified computational model is developed, which allows for systematic parameter variations. The model is based on modal reduction of the airfoil structure. An unsteady aerodynamic model is applied based on the results of numerical flow simulations. Investigation of aeroelastic stability leads to the usual phenomena of a conventional airfoil. Additionally, bending flutter occurs at high blowing rates of the Coanda stream and low velocities. |
| Autor(en) | Krukow, Ian | Dinkler, Dieter |
|---|---|
| Titel | A Reduced-Order Model for Aeroelastic Studies on Circulation Controlled Wings |
| Herausgeber | GACM, Hamburg |
| Erscheinungsjahr | 2013 |
| Abstract | Take-off and landing of commercial aircraft on short runways in urban areas are possible, if noise emission and minimum flight velocity are adjusted accordingly. The loss of lift due to the lower velocity has to be outweighed by active high-lift devices. A possible approach to achieve the necessary increase in lift is the application of the Coanda effect, which is able to avoid flow separation at the trailing edge at high flap angles. With the application of circulation control, the aeroelasticity has to be taken into account, because the deformation of the airfoil may reduce the increase in lift significantly. For numerical simulations of extensive case studies, a reduced-order model is developed, which includes the effect of the Coanda stream on the generation of lift in a parametrised form. The reduced-order model can be integrated into a simplified flight dynamics model. Developing the aeroelastic model, it is necessary to couple the aerodynamics of the wing profile with the structure of the elastic airfoil. The aerodynamic model is derived from numerical simulations of the flow around the profile with the TAU-code. For a broad range of parameters, the quasi-steady flow as well as harmonic oscillations are simulated depending on the angle of attack, the flap angle and the momentum coefficient of the Coanda stream. From these simulations, the aerodynamic coefficients for lift and momentum are identified and described by a polynomial smoothing function, so that a closed mathematical form is obtained. The two-dimensional model is adapted to the three dimensional wing using the strip theory. The structure behaviour is described by means of a full 3-D-discretization with the finite element method and reduced by a modal transformation. The connection between the aerodynamic forces and the structure model is done by projecting the load distribution onto the eigenmodes of the structure. With the modal transformation, the parameters of the full-scale model, e.g. the air speed and the momentum coefficient of the Coanda stream, are preserved as well as the non-linearities in the equations of motion resulting from the non-linear aerodynamic model. Basic applications of the model are exemplified. |
| Autor(en) | Sommerwerk, Kay | Haupt, Matthias | Horst, Peter |
|---|---|
| Titel | FSI of High Performance High-Lift Devices with Circulation Control via Conditioned Coanda-Jets |
| Herausgeber | Proceedings of V Conference on Computational Methods for Coupled Problems in Science and Engineering, June 17-19, Ibiza, Spain |
| Erscheinungsjahr | 2013 |
| Abstract | Current transport aircraft are limited to airports with comparatively long runways for take-off and landing. An aircraft with short take-off and landing capabilities is under investigation at the Collaborative Research Center 880. The aircraft employs circulation controlled high lift devices where high velocity air is blown through a slot in front of the flap. These high performance high-lift devices allow take-off and landing of the aircraft at runways of 800 m length. The curved flap leading edge induces a Coanda effect with the jet resulting in an attached flow up to the tip of the flap even at high deflection angles of up to 85°. Examination of the aeroelasticity of the wing is of high importance because of the sensitivity of the Coanda effect to perturbation through deformation and consequential change in flow. The large pressure gradients can play a significant role in the effective use of this jet system. Preliminary studies have shown an influence on aerodynamic performance due to slot deformation. Small changes in the aerodynamic characteristics can have adverse effects on the stall behavior. A flap section model of the wing is used to analyze the performance for several flight states. This high detail model allows capturing fine effects over the whole wing chord and on the slot region while still including wing deformations. The aerodynamic performance of the aeroelastic flap section model is compared to the characteristics of the rigid airfoil. The analyzed flight states give an insight into the influence of the deformation on the flow. Additionally the effects of jet momentum variation on aerodynamics is shown and the dominant stall phenomena presented. The local relative change in pressure can reach values between 10 and 20 % and has an influence on the stall behavior of the section. The change in aerodynamic performance illustrates the influence of small deformations on the sensitive circulation control. |
| Autor(en) | Sommerwerk, Kay | Haupt, Matthias | Horst, Peter |
|---|---|
| Titel | Aeroelastic Performance Assessment of a Wing with Coanda Effect Circulation Control via Fluid-Structure Interaction |
| Herausgeber | AIAA 2013-2791, 31st AIAA Applied Aerodynamics Conference, June 24-27, San Diego, USA |
| Erscheinungsjahr | 2013 |
| Abstract | Airports with comparatively long runways are needed for current transport aircraft for takeoff and landing. The necessary runway length as a basic characteristic limits the use of smaller airports with available capacity. An aircraft with short takeoff and landing capabilities is under investigation at the Collaborative Research Center SFB 880. The aircraft employs circulation controlled high lift devices allowing short takeoff and landing. High velocity air is blown through a slot in front of the flaps to interact with the oncoming boundary layer. The curved flap leading edge behind the slot induces a Coanda effect resulting in an attached flow up to the tip of the flap even at high deflection angles of up to 85°. Evaluation of the aeroelasticity of the wing is of high importance due to the sensitivity of the Coanda effect to perturbation through deformation and consequential change in flow. Perturbation sources are the deformation of the slot lip as well as the global wing deflection. High fidelity fluid structure interaction simulation are used to identify the global and local effects of elastic models. A flap sectional model is used to capture the local slot deformation influence, whereas a complete wing model takes the global deformations into account. The slot stiffness has an influence on the aerodynamic performance, depending on the jet momentum. The small global wing deformations for the analyzed wing have a noticeable but small influence on the aerodynamics. |
| Autor(en) | Krukow, Ian | Dinkler, Dieter | Haupt, Matthias |
|---|---|
| Titel | Entwicklung eines reduzierten Modells für die Beurteilung der Aeroelastik eines Tragflügels mit aktivem Hochauftriebssystem |
| Herausgeber | 61. Deutscher Luft- und Raumfahrtkongress, Berlin |
| Erscheinungsjahr | 2012 |
| Abstract | Mit dem Einsatz aktiver Zirkulationskontrollen ist eine im Einzelfall erhebliche Verkürzung der Start- und Landebahnlängen von modernen Flugzeugen möglich. Im vorliegenden Aufsatz soll der Einfluss der Zirkulationskontrolle auf das aeroelastische Verhalten einer Flugzeugtragfläche untersucht werden. Für die numerische Analyse wird ein vereinfachendes Berechnungsmodell vorgestellt, mit dem systematische Parametervariationen möglich sind. Grundlage des Modells ist die Modellreduktion mit Hilfe der Modal-Analyse, sodass eine effiziente Durchführung numerischer Studien sowie die Berücksichtigung der Aeroelastik in einem weiterführenden flugmechanischen Modell möglich ist. |
| Autor(en) | Krukow, Ian | Dinkler, Dieter | Haupt, Matthias |
|---|---|
| Titel | Modellreduktion für die Aeroelastik eines Flügels mit aktivem Hochauftriebssystem |
| Herausgeber | 61. Deutscher Luft- und Raumfahrtkongress, Berlin |
| Erscheinungsjahr | 2012 |
| Abstract | Mit dem Einsatz aktiver Zirkulationskontrollen ist eine im Einzelfall erhebliche Verkürzung der Start- und Landebahnlängen von modernen Flugzeugen möglich. In der vorliegenden Arbeit soll der Einfluss der Zirkulationskontrolle auf das aeroelastische Verhalten einer Flugzeugtragfläche untersucht werden. Für die numerische Analyse wird ein vereinfachendes Berechnungsmodell vorgestellt, mit dem systematische Parametervariationen möglich sind. Grundlage des Modells ist die Modellreduktion mit Hilfe der Modal-Analyse, sodass eine effiziente Durchführung numerischer Studien sowie die Berücksichtigung der Aeroelastik in einem weiterführenden flugmechanischen Modell möglich ist. Das Poster gibt einen Überblick über die entwickelten Modelle und deren Ergebnisse. Eine ausführliche Darstellung ist im zugehörigen Konferenzartikel zu finden. |
| Autor(en) | Sommerwerk, Kay | Haupt, Matthias |
|---|---|
| Titel | Structural Sizing of a CFRP Wing with Coanda Flaps via CFD-CSM Coupling |
| Herausgeber | Proceedings of 61. Deutscher Luft- und Raumfahrtkongress, Berlin |
| Erscheinungsjahr | 2012 |
| Abstract | Preliminary aircraft design suffers from the lack of detailed models to verify the assumed parameters of loads and structures, which may have a high impact on the accuracy of the solutions. A 100 PAX commercial aircraft with short take-off and landing capabilities of 800 meters with circulation controlled high lift devices is under investigation at the Collaborative Research Centre SFB 880. High velocity air is blown through a slot in front of the high lift device thus inducing a Coanda effect on the curved flap leading edge. This leads to an attached flow at high flap angles inducing very high lift coefficients. In this paper, a global wing analysis is conducted and the results are compared with preliminary extrapolations. Several designs for the air feed system integration are proposed and examined regarding weight and stiffness characteristics on a representative high lift device section model. Fluid structure coupling is employed during the analyses to transfer aerodynamic loads and structural displacements to determine the aero-elastic impact of the slot stiffness on the Coanda effect during landing. The attained aerodynamic performance results and structural characteristics of each configuration are compared and the advantages discussed. |