The Experts below are selected from a list of 291 Experts worldwide ranked by ideXlab platform
Pierluigi Della Vecchia - One of the best experts on this subject based on the ideXlab platform.
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flight tests performances and flight certification of a twin Engine light aircraft
Journal of Aircraft, 2011Co-Authors: Fabrizio Nicolosi, Agostino De Marco, Pierluigi Della VecchiaAbstract:This paper deals with flight test activities performed on P2006T, a twin-Engine light aircraft recently designed and produced by Tecnam. Research activities and flight tests have been conducted during the flight certification of P2006T for the normal category under CS23. All the acquired data and flight results presented have been focused on both aircraft certification and on aircraft performances, stability and flight qualities measurement. The data have been acquired through a light, accurate and reliable flight instrumentation available at DIAS (Department of Aerospace Engineering). Some flight data about aircraft leveled speed, stall speed, climb characteristics and ground performances (take-off and landing) will be presented. After preliminary flight tests, winglets have been designed and added to the final configuration in order to obtain good climb performances also in OEI (One Engine Inoperative) conditions. Accurate stall tests have been performed in all configurations and influence of both entry-rate and load factor on stall speed have been highlighted. Excellent ground performances have been measured with short take-off and landing distances compared with similar airplanes. All measured flight performances can be considered very good for this aircraft category and have been used to demonstrate aircraft safety and to obtain CS23 certification.
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Flight Tests, Performances and Flight Certification of a Twin-Engine Light Aircraft
Journal of Aircraft, 2011Co-Authors: Fabrizio Nicolosi, Agostino De Marco, Pierluigi Della VecchiaAbstract:This paper deals with flight test activities performed on P2006T, a twin-Engine light aircraft recently designed and produced by Tecnam. Research activities and flight tests have been conducted during the flight certification of P2006T for the normal category under CS23. All the acquired data and flight results presented have been focused on both aircraft certification and on aircraft performances, stability and flight qualities measurement. The data have been acquired through a light, accurate and reliable flight instrumentation available at DIAS (Department of Aerospace Engineering). Some flight data about aircraft leveled speed, stall speed, climb characteristics and ground performances (take-off and landing) will be presented. After preliminary flight tests, winglets have been designed and added to the final configuration in order to obtain good climb performances also in OEI (One Engine Inoperative) conditions. Accurate stall tests have been performed in all configurations and influence of both entry-rate and load factor on stall speed have been highlighted. Excellent ground performances have been measured with short take-off and landing distances compared with similar airplanes. All measured flight performances can be considered very good for this aircraft category and have been used to demonstrate aircraft safety and to obtain CS23 certification.
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Flight tests, performances, and flight certification of a twin-Engine light aircraft
'American Institute of Aeronautics and Astronautics (AIAA)', 2011Co-Authors: F. Nicolosi, Agostino De Marco, Pierluigi Della VecchiaAbstract:This paper deals with flight-test activities performed on the P2006T, a twin-Engine light aircraft recently designed and produced by Tecnam. Research activities and flight tests have been conducted during the flight certification of the P2006T for the normal category under European regulation CS-23. All the acquired data and flight results presented have been focused on both aircraft certification and aircraft performance, stability, and flight quality measurements. The data have been acquired through light, accurate, and reliable flight instrumentation available at the University of Naples “Federico II” department of aerospace Engineering. Some flight data about aircraft leveled speed, stall speed, climb characteristics, and ground performances (takeoff and landing) will be presented. After preliminary flight tests, winglets have been designed and added to the final configuration in order to obtain good climb performances in one-Engine Inoperative conditions. Accurate stall tests have been performed in all configurations, and the influence of both the entry rate and the load factor on stall speed have been highlighted. Excellent ground performances have been measured with short takeoff and landing distances compared with similar airplanes. All measured flight performances can be considered very good for this aircraft category and have been used to demonstrate aircraft safety and to obtain CS-23 certification
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Flight tests of a twin-Engine aircraft: performances, stability and parameter estimation
2009Co-Authors: F. Nicolosi, Agostino De Marco, Pierluigi Della VecchiaAbstract:The present paper deals with flight test activities performed on P2006T twin-Engine light aircraft recently designed and produced by Tecnam(www.tecnam.com). Research activities and flight tests have been performed during the flight certification (C.S. 23) of P2006 aircraft. All the acquired data and flight results presented have been focused to both aircraft certification and to measure and optimize aircraft performances and flight qualities. All flight data have been acquired through a light, accurate and reliable flight instrumentation avail-able at DIAS(Department of Aerospace Engineering). The first part of the paper deals with flight tests that have been performed to measure and acquire aircraft flight performances. Some flight data about aircraft levelled speed, stall speed, climb characteristics and ground performances (take-off and landing) will be presented. After preliminary flight tests, winglet have been designed and added to the final configuration to obtain good climb performances also in OEI(One Engine Inoperative) condition. Excellent ground performances have been measured with short take-off and landing distances compared to aircraft belonging to the same category. All measured flight performances can be considered very good for this air-craft category and have been used to demonstrate aircraft safety and to obtain C.S. 23 certifi-cation. The second part of the paper deals with flight test activities that have been performed to obtain a quantitative measurement of aircraft flight qualities (i.e. dynamic longitudinal stability characteristics) and to perform a complete aircraft parameter estimation. Through a dedicated set of performed manoeuvres and consequent acquired flight data the longitudinal stability derivatives have been estimated through MLM (maximum likelihood method). A mat-lab code with the longitudinal equation of motion and with classical aircraft dynamics equa-tions has been used to reconstruct the aircraft aerodynamic model
Ralf Rudnik - One of the best experts on this subject based on the ideXlab platform.
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Aerodynamic Analysis of a STOL Propeller Aircraft with Active High-Lift and Control Surface Systems
Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 2020Co-Authors: Dennis Keller, Ralf RudnikAbstract:The aerodynamic properties of a state-of-the-art short take-off and landing aircraft design with circulation control and slipstream deflection in landing configuration have been investigated via RANS simulations. The present paper summarizes the findings concerning one Engine Inoperative conditions (OEI), active control surface design, and ground effect. It is shown that the unfavorable aircraft’s aerodynamic characteristics under OEI conditions, including a degraded maximum lift coefficient and extraordinarily high yawing moments, can be improved via passive measures, such as nacelle strakes and tail fences. The resulting requirements for lateral control forces can be fulfilled by the use of circulation controlled rudder and ailerons. Simulations of the 3D configuration in ground proximity yield a beneficial effect on the lift coefficient despite contrary indications from 2D computations. Furthermore, the simulations show a significant pitch down tendency due to ground proximity.
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Investigation and improvement of directional stability and control of a propeller-driven STOL aircraft
CEAS Aeronautical Journal, 2019Co-Authors: Dennis Keller, Ralf RudnikAbstract:The scope of this paper is to investigate and improve the aerodynamic properties of a propeller driven state-of-the-art active high-lift configuration in lateral motion. 3D RANS simulations of the landing configuration with circulation control and slipstream deflection under crosswind, and one Engine Inoperative (OEI) conditions were performed. The configuration shows directionally unstable behavior at small sideslip angles and high yawing moment production under OEI conditions. Flowfield analyses indicate that both can be attributed to wake-tail interference effects caused by slipstream–vortex interaction. The integration of tail fences at the rear of the fuselage leads to considerable improvements for both conditions.
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Investigation and Improvement of Directional Stability and Control under Slipstream Effects
2018 AIAA Aerospace Sciences Meeting, 2018Co-Authors: Dennis Keller, Ralf RudnikAbstract:The scope of this paper is to investigate and improve the aerodynamic properties of a propeller driven active high-lift configuration in lateral motion. Therefore, results of 3D RANS simulations of a landing configuration with circulation control and slipstream deflection under crosswind and one Engine Inoperative (OEI) conditions are discussed. The configuration shows directionally unstable behavior at small sideslip angles and high yawing moment production under OEI conditions. Flowfield analysis indicate that both can be attributed to wake-tail interference effects, caused by slipstream-vortex interaction. The integration of tail fences at the rear of the fuselage leads to considerable improvements under both conditions.
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Numerical investigations of aerodynamic properties of a propeller blown circulation control system on a high wing aircraft
CEAS Aeronautical Journal, 2016Co-Authors: Dennis Keller, Ralf RudnikAbstract:The contribution gives an overview over a wide range of CFD simulations, which were performed in the course of the German collaborative research center 880 to investigate the aerodynamic properties of a complete turboprop powered transport aircraft in landing configuration with a circulation control high-lift system. The main purpose of the contribution is to highlight aerodynamic and flight mechanical aspects of the integration of lift augmentation technologies into the design of a short take-off and landing aircraft concept. In this context, the influence of Engine nacelles and thrust on the stall behavior and the following improvements due to the use of a nacelle strake are discussed. Furthermore, static longitudinal and lateral stability as well as the dynamic longitudinal stability are investigated. While circulation control itself has a rather small impact on the stability, the impact of Engine thrust in conjunction with circulation control is considerable. In addition, the one Engine Inoperative case was simulated. For some flow and Engine conditions, the resulting yawing moments are more than twice as high as the actual yawing moments due to asymmetric thrust.
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Numerical Investigation of Engine Effects on a Transport Aircraft with Circulation Control
Journal of Aircraft, 2015Co-Authors: Dennis Keller, Ralf RudnikAbstract:The scope of this paper is to illustrate the installation effects of a turboprop Engine on a high-lift configuration of a short takeoff and landing aircraft with circulation control. In addition to the influence on the wing performance, the impact on the longitudinal static stability of the aircraft is also investigated. Furthermore, critical failure cases, namely one Engine Inoperative, as well as an asymmetric circulation control failure, are assessed. Therefore, steady computational-fluid-dynamics calculations based on the Reynolds-averaged Navier–Stokes equations were performed. The propeller is modeled with an actuator-disk approach. The results show strong potential of increasing lift by synergy effects between circulation control and propeller slipstream. However, the longitudinal stability and controllability are adversely affected. Regarding the case of one Engine Inoperative, the resulting yawing moments are twice as high as the actual yawing moments from the asymmetric thrust and are therefore ...
Dennis Keller - One of the best experts on this subject based on the ideXlab platform.
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Aerodynamic Analysis of a STOL Propeller Aircraft with Active High-Lift and Control Surface Systems
Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 2020Co-Authors: Dennis Keller, Ralf RudnikAbstract:The aerodynamic properties of a state-of-the-art short take-off and landing aircraft design with circulation control and slipstream deflection in landing configuration have been investigated via RANS simulations. The present paper summarizes the findings concerning one Engine Inoperative conditions (OEI), active control surface design, and ground effect. It is shown that the unfavorable aircraft’s aerodynamic characteristics under OEI conditions, including a degraded maximum lift coefficient and extraordinarily high yawing moments, can be improved via passive measures, such as nacelle strakes and tail fences. The resulting requirements for lateral control forces can be fulfilled by the use of circulation controlled rudder and ailerons. Simulations of the 3D configuration in ground proximity yield a beneficial effect on the lift coefficient despite contrary indications from 2D computations. Furthermore, the simulations show a significant pitch down tendency due to ground proximity.
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Investigation and improvement of directional stability and control of a propeller-driven STOL aircraft
CEAS Aeronautical Journal, 2019Co-Authors: Dennis Keller, Ralf RudnikAbstract:The scope of this paper is to investigate and improve the aerodynamic properties of a propeller driven state-of-the-art active high-lift configuration in lateral motion. 3D RANS simulations of the landing configuration with circulation control and slipstream deflection under crosswind, and one Engine Inoperative (OEI) conditions were performed. The configuration shows directionally unstable behavior at small sideslip angles and high yawing moment production under OEI conditions. Flowfield analyses indicate that both can be attributed to wake-tail interference effects caused by slipstream–vortex interaction. The integration of tail fences at the rear of the fuselage leads to considerable improvements for both conditions.
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Investigation and Improvement of Directional Stability and Control under Slipstream Effects
2018 AIAA Aerospace Sciences Meeting, 2018Co-Authors: Dennis Keller, Ralf RudnikAbstract:The scope of this paper is to investigate and improve the aerodynamic properties of a propeller driven active high-lift configuration in lateral motion. Therefore, results of 3D RANS simulations of a landing configuration with circulation control and slipstream deflection under crosswind and one Engine Inoperative (OEI) conditions are discussed. The configuration shows directionally unstable behavior at small sideslip angles and high yawing moment production under OEI conditions. Flowfield analysis indicate that both can be attributed to wake-tail interference effects, caused by slipstream-vortex interaction. The integration of tail fences at the rear of the fuselage leads to considerable improvements under both conditions.
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Numerical investigations of aerodynamic properties of a propeller blown circulation control system on a high wing aircraft
CEAS Aeronautical Journal, 2016Co-Authors: Dennis Keller, Ralf RudnikAbstract:The contribution gives an overview over a wide range of CFD simulations, which were performed in the course of the German collaborative research center 880 to investigate the aerodynamic properties of a complete turboprop powered transport aircraft in landing configuration with a circulation control high-lift system. The main purpose of the contribution is to highlight aerodynamic and flight mechanical aspects of the integration of lift augmentation technologies into the design of a short take-off and landing aircraft concept. In this context, the influence of Engine nacelles and thrust on the stall behavior and the following improvements due to the use of a nacelle strake are discussed. Furthermore, static longitudinal and lateral stability as well as the dynamic longitudinal stability are investigated. While circulation control itself has a rather small impact on the stability, the impact of Engine thrust in conjunction with circulation control is considerable. In addition, the one Engine Inoperative case was simulated. For some flow and Engine conditions, the resulting yawing moments are more than twice as high as the actual yawing moments due to asymmetric thrust.
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Numerical Investigation of Engine Effects on a Transport Aircraft with Circulation Control
Journal of Aircraft, 2015Co-Authors: Dennis Keller, Ralf RudnikAbstract:The scope of this paper is to illustrate the installation effects of a turboprop Engine on a high-lift configuration of a short takeoff and landing aircraft with circulation control. In addition to the influence on the wing performance, the impact on the longitudinal static stability of the aircraft is also investigated. Furthermore, critical failure cases, namely one Engine Inoperative, as well as an asymmetric circulation control failure, are assessed. Therefore, steady computational-fluid-dynamics calculations based on the Reynolds-averaged Navier–Stokes equations were performed. The propeller is modeled with an actuator-disk approach. The results show strong potential of increasing lift by synergy effects between circulation control and propeller slipstream. However, the longitudinal stability and controllability are adversely affected. Regarding the case of one Engine Inoperative, the resulting yawing moments are twice as high as the actual yawing moments from the asymmetric thrust and are therefore ...
Le Graverend Jean-briac - One of the best experts on this subject based on the ideXlab platform.
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Experimental analysis and modeling of the effects of high temperature incursions on the mechanical behavior of a single crystal superalloy for turbines blades
2013Co-Authors: Le Graverend Jean-briacAbstract:Ce travail s'inscrit dans le contexte de la modélisation et de la prévision de la durée de vie des aubes de turbine haute pression des turbines à gaz. Ces pièces sont réalisées en superalliage monocristallin base nickel tel que le MC2, matériau principal de l'étude. En service, ces dernières sont soumises à des conditions extrêmes de température et de contrainte. Des régimes d'urgence, dits O.E.I. (.One Engine Inoperative.), peuvent aussi survenir sur un hélicoptère bi-moteur : un des deux moteurs s'arrête ce qui provoque une augmentation de la température en sortie de chambre de combustion pour le moteur restant en fonctionnement. Dans le cadre de ce travail, le comportement anisotherme en fluage et en fatigue/fluage du superalliage monocristallin a été étudié afin de déterminer les répercussions des surchauffes à 1200. sur le comportement mécanique ultérieur à 1050. Il a pu être déterminé que le temps de pré-endommagement avant la surchauffe joue un rôle capital vis-à-vis de la durée de vie post-surchauffe. Cette influence est très dépendante de l'état microstructural du matériau sur lequel est réalisée la surchauffe (morphologie des précipités γ ', contraintes de cohérence entre les phases γ et γ '). Du point de vue des mécanismes d'endommagement, il a aussi été constaté que le niveau de température a une importance majeure en modifiant les contraintes de cohérence entre les deux phases γ et γ '. L'état microstructural jouant un rôle majeur sur la durée de vie lors des essais isothermes et anisothermes, une étude de l'évolution de la microstructure γ /γ' autour des particules de phase intermétallique μ a été faite, ainsi qu'une mesure expérimentale de l'évolution de la porosité, mesurée par des analyses tomographiques grâce à des essais de fluage multi-interrompus à haute température. Ceci a permis d'aboutir à un paramètre de dommage, à la frontière entre métallurgie et mécanique, prenant en compte les évolutions microstructurales. La coalescence orientée se déroulant à haute température, connue sous le nom de mise en radeaux, a une forte influence sur le comportement et l'endommagement des superalliages monocristallins. Ainsi, un nouveau modèle de mise en radeaux, prenant en compte la vitesse de sollicitation, a été implémenté dans le modèle de plasticité cristalline couplé comportement/endommagement Polystar. Ceci a permis d'améliorer la modélisation des essais longs. D'autres modifications ont été effectuées afin d'améliorer la modélisation lors des essais cycliques et de relaxation. Ce nouveau modèle a été testé et validé sur une éprouvette bi-entaillée générant des champs mécaniques multiaxiaux pendant un essai de fluage complexe anisothermeThis work is in the context of modeling and predicting the life of high pressure turbine blades of gas turbines. These components are made of nickel base single crystal superalloy such as the studied material MC2. Under operating conditions, they can be submitted to extreme stress and temperature conditions such as O.E.I. (.One Engine Inoperative.) which can also occur on a twin-Engine helicopter : one Engine stops which causes an increase in the outlet temperature of the combustion chamber for the remaining Engine. In this work, the non-isothermal creep and creep/fatigue behaviors of single crystal superalloy have been studied to determine the impact of overheating at 1200. on the subsequent mechanical behavior at 1050 .. It has been determined that the prior thermomechanical degradation before an overheating plays an important role on the remaining life fraction. This influence is very dependent on the microstructural state of the material on which is performed the overheating (precipitate morphology of γ', coherency stress between the γ and γ' phases). From the damagemechanisms point of view, it was also found that the temperature level has a major importance in changing the coherency stresses between these two phases. The microstructural state plays a major role on the isothermal and non-isothermal life. Thus, the evolutions of the /' microstructure around the intermetallic μ phase particles have been studied as the porosity (determined by tomographic analysis through multi-interrupted creep tests at high temperature) which has led to a damage parameter taking into account microstructural evolutions and at the borderline between metallurgy and mechanics. Since the γ' directional coarsening is known to have an impact on the mechanical behavior at high temperature, a new model taking into account the γ' rafting has been designed. It takes into account the strain rate sensitivity of the γ' rafting and it was implemented in the coupled behavior/damage model of crystal plasticity named Polystar model. This has improved the modeling of long tests. Other changes were made to improve the cyclic and relaxation behaviors. This new model has been tested and validated on a notched specimen generating multiaxial mechanical fields during a non-isothermal complex creep test
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Etude et modélisation des effets d'incursion à très haute température sur le comportement mécanique d'un superalliage monocristallin pour aubes de turbine
HAL CCSD, 2013Co-Authors: Le Graverend Jean-briacAbstract:This work is in the context of modeling and predicting the life of high pressure turbine blades of gas turbines. These components are made of nickel base single crystal superalloy such as the studied material MC2. Under operating conditions, they can be submitted to extreme stress and temperature conditions such as O.E.I. (.One Engine Inoperative.) which can also occur on a twin-Engine helicopter : one Engine stops which causes an increase in the outlet temperature of the combustion chamber for the remaining Engine. In this work, the non-isothermal creep and creep/fatigue behaviors of single crystal superalloy have been studied to determine the impact of overheating at 1200. on the subsequent mechanical behavior at 1050 .. It has been determined that the prior thermomechanical degradation before an overheating plays an important role on the remaining life fraction. This influence is very dependent on the microstructural state of the material on which is performed the overheating (precipitate morphology of γ', coherency stress between the γ and γ' phases). From the damagemechanisms point of view, it was also found that the temperature level has a major importance in changing the coherency stresses between these two phases. The microstructural state plays a major role on the isothermal and non-isothermal life. Thus, the evolutions of the /' microstructure around the intermetallic μ phase particles have been studied as the porosity (determined by tomographic analysis through multi-interrupted creep tests at high temperature) which has led to a damage parameter taking into account microstructural evolutions and at the borderline between metallurgy and mechanics. Since the γ' directional coarsening is known to have an impact on the mechanical behavior at high temperature, a new model taking into account the γ' rafting has been designed. It takes into account the strain rate sensitivity of the γ' rafting and it was implemented in the coupled behavior/damage model of crystal plasticity named Polystar model. This has improved the modeling of long tests. Other changes were made to improve the cyclic and relaxation behaviors. This new model has been tested and validated on a notched specimen generating multiaxial mechanical fields during a non-isothermal complex creep test.Ce travail s'inscrit dans le contexte de la modélisation et de la prévision de la durée de vie des aubes de turbine haute pression des turbines à gaz. Ces pièces sont réalisées en superalliage monocristallin base nickel tel que le MC2, matériau principal de l'étude. En service, ces dernières sont soumises à des conditions extrêmes de température et de contrainte. Des régimes d'urgence, dits O.E.I. (.One Engine Inoperative.), peuvent aussi survenir sur un hélicoptère bi-moteur : un des deux moteurs s'arrête ce qui provoque une augmentation de la température en sortie de chambre de combustion pour le moteur restant en fonctionnement. Dans le cadre de ce travail, le comportement anisotherme en fluage et en fatigue/fluage du superalliage monocristallin a été étudié afin de déterminer les répercussions des surchauffes à 1200. sur le comportement mécanique ultérieur à 1050. Il a pu être déterminé que le temps de pré-endommagement avant la surchauffe joue un rôle capital vis-à-vis de la durée de vie post-surchauffe. Cette influence est très dépendante de l'état microstructural du matériau sur lequel est réalisée la surchauffe (morphologie des précipités γ ', contraintes de cohérence entre les phases γ et γ '). Du point de vue des mécanismes d'endommagement, il a aussi été constaté que le niveau de température a une importance majeure en modifiant les contraintes de cohérence entre les deux phases γ et γ '. L'état microstructural jouant un rôle majeur sur la durée de vie lors des essais isothermes et anisothermes, une étude de l'évolution de la microstructure γ /γ' autour des particules de phase intermétallique μ a été faite, ainsi qu'une mesure expérimentale de l'évolution de la porosité, mesurée par des analyses tomographiques grâce à des essais de fluage multi-interrompus à haute température. Ceci a permis d'aboutir à un paramètre de dommage, à la frontière entre métallurgie et mécanique, prenant en compte les évolutions microstructurales. La coalescence orientée se déroulant à haute température, connue sous le nom de mise en radeaux, a une forte influence sur le comportement et l'endommagement des superalliages monocristallins. Ainsi, un nouveau modèle de mise en radeaux, prenant en compte la vitesse de sollicitation, a été implémenté dans le modèle de plasticité cristalline couplé comportement/endommagement Polystar. Ceci a permis d'améliorer la modélisation des essais longs. D'autres modifications ont été effectuées afin d'améliorer la modélisation lors des essais cycliques et de relaxation. Ce nouveau modèle a été testé et validé sur une éprouvette bi-entaillée générant des champs mécaniques multiaxiaux pendant un essai de fluage complexe anisotherm
Anna Kröhnert - One of the best experts on this subject based on the ideXlab platform.
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Numerical Investigation of Unsteady Tangential Blowing at the Rudder of a Vertical Tailplane Airfoil
Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 2016Co-Authors: Anna KröhnertAbstract:A numerical 2D investigation of a vertical tailplane airfoil using active flow control with tangential blowing over the rudder shoulder is conducted. The aim of the flow control application is to increase the maximum lift or side force, which can be created by the vertical tailplane, at critical flight conditions like the one-Engine-Inoperative failure case. In this case the rudder is highly deflected, leading to a large separation on the rudder without blowing. With constant tangential blowing at the rudder shoulder it was shown that fully attached flow can be achieved. To increase the efficiency, pulsed blowing is applied in the present study, leading to a similar increase in the lift coefficient at a reduced actuation mass flow rate requirement. Parameters like the blowing momentum coefficient and the dimensionless frequency are varied and the results are compared to those of the flow calculations with constant blowing. It is observed that pulsed blowing with a small momentum coefficient leads to a strong increase in the lift coefficient compared to constant blowing. The resulting lift increment depends on the dimensionless frequency selected.
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Numerical Investigation of Tangential Blowing at the Rudder of a Vertical Tailplane Airfoil
32nd AIAA Applied Aerodynamics Conference, 2014Co-Authors: Anna KröhnertAbstract:A numerical 2D investigation of a vertical tailplane airfoil using active flow control with tangential blowing over the rudder shoulder is conducted. The intention of the flow control application is to increase the maximum lift or side force which can be created by the vertical tailplane at critical conditions like the one-Engine-Inoperative failure case. On the highly deflected rudder a large separation can be found without blowing. With tangential blowing it is shown that fully attached flow can be achieved. The flow simulations performed are based on the Reynolds-averaged Navier-Stokes equations. The parameters momentum coeffi�cient, slot height and angle of attack of the oncoming flow are varied to assess sensitivities and the influence on the results. Furthermore, the influence of a geometric detail in the vicinity of the slot exit is investigated, namely the existence or omission of a step behind the slot exit. Finally, the influence of the turbulence model is studied where besides the Spalart and Allmaras turbulence model with rotational and curvature correction (SARC) also the SAO and RSM turbulence models are applied.