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Matthias Bauer
Navasto GmbH, 10553 Berlin, Germany

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Journal article
Published: 01 January 2019 in AIAA Journal
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ACS Style

Philipp Schloesser; Vitaly Soudakov; Matthias Bauer; Jochen Wild. Active Separation Control at the Pylon-Wing Junction of a Real-Scale Model. AIAA Journal 2019, 57, 132 -141.

AMA Style

Philipp Schloesser, Vitaly Soudakov, Matthias Bauer, Jochen Wild. Active Separation Control at the Pylon-Wing Junction of a Real-Scale Model. AIAA Journal. 2019; 57 (1):132-141.

Chicago/Turabian Style

Philipp Schloesser; Vitaly Soudakov; Matthias Bauer; Jochen Wild. 2019. "Active Separation Control at the Pylon-Wing Junction of a Real-Scale Model." AIAA Journal 57, no. 1: 132-141.

Journal article
Published: 04 September 2017 in Aircraft Engineering and Aerospace Technology
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The area behind the engine/wing junction of conventional civil aircraft configurations with underwing-mounted turbofans is susceptible to local flow separation at high angles of attack, which potentially impacts maximum lift performance of the aircraft. This paper aims to present the design, testing and optimization of two distinct systems of fluidic actuation dedicated to reduce separation at the engine/wing junction. Active flow control applied at the unprotected leading edge inboard of the engine pylon has shown considerable potential to alleviate or even eliminate local flow separation, and consequently regain maximum lift performance. Two actuator systems, pulsed jet actuators with and without net mass flux, are tested and optimized with respect to an upcoming large-scale wind tunnel test to assess the effect of active flow control on the flow behavior. The requirements and parameters of the flow control hardware are set by numerical simulations of project partners. The results of ground test show that full modulation of the jets of the non-zero mass flux actuator is achieved. In addition, it could be shown that the required parameters can be satisfied at design mass flow, and that pressure levels are within bounds. Furthermore, a new generation of zero-net mass flux actuators with improved performance is presented and described. This flow control system includes the actuator devices, their integration, as well as the drive and control electronics system that is used to drive groups of actuators. The originality is given by the application of the two flow control systems in a scheduled large-scale wind tunnel test.

ACS Style

Philipp Schloesser; Michael Meyer; Martin Schueller; Perez Weigel; Matthias Bauer. Fluidic actuators for separation control at the engine/wing junction. Aircraft Engineering and Aerospace Technology 2017, 89, 709 -718.

AMA Style

Philipp Schloesser, Michael Meyer, Martin Schueller, Perez Weigel, Matthias Bauer. Fluidic actuators for separation control at the engine/wing junction. Aircraft Engineering and Aerospace Technology. 2017; 89 (5):709-718.

Chicago/Turabian Style

Philipp Schloesser; Michael Meyer; Martin Schueller; Perez Weigel; Matthias Bauer. 2017. "Fluidic actuators for separation control at the engine/wing junction." Aircraft Engineering and Aerospace Technology 89, no. 5: 709-718.

Journal article
Published: 19 October 2016 in Aerospace
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This paper discusses wind tunnel test results aimed at advancing active flow control technology to increase the aerodynamic efficiency of an aircraft during take-off. A model of the outer section of a representative civil airliner wing was equipped with two-stage fluidic actuators between the slat edge and wing tip, where mechanical high-lift devices fail to integrate. The experiments were conducted at a nominal take-off Mach number of M = 0.2. At this incidence velocity, separation on the wing section, accompanied by increased drag, is triggered by the strong slat edge vortex at high angles of attack. On the basis of global force measurements and local static pressure data, the effect of pulsed blowing on the complex flow is evaluated, considering various momentum coefficients and spanwise distributions of the actuation effort. It is shown that through local intensification of forcing, a momentum coefficient of less than cμ=0.6% suffices to offset the stall by 2.4°, increase the maximum lift by more than 10% and reduce the drag by 37% compared to the uncontrolled flow.

ACS Style

Matthias Bauer; Thomas Grund; Wolfgang Nitsche; Vlad Ciobaca. Wing Tip Drag Reduction at Nominal Take-Off Mach Number: An Approach to Local Active Flow Control with a Highly Robust Actuator System. Aerospace 2016, 3, 36 .

AMA Style

Matthias Bauer, Thomas Grund, Wolfgang Nitsche, Vlad Ciobaca. Wing Tip Drag Reduction at Nominal Take-Off Mach Number: An Approach to Local Active Flow Control with a Highly Robust Actuator System. Aerospace. 2016; 3 (4):36.

Chicago/Turabian Style

Matthias Bauer; Thomas Grund; Wolfgang Nitsche; Vlad Ciobaca. 2016. "Wing Tip Drag Reduction at Nominal Take-Off Mach Number: An Approach to Local Active Flow Control with a Highly Robust Actuator System." Aerospace 3, no. 4: 36.

Conference paper
Published: 13 June 2014 in 32nd AIAA Applied Aerodynamics Conference
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ACS Style

Michael Meyer; Wolfgang Machunze; Matthias Bauer. Towards the Industrial Application of Active Flow Control in Civil Aircraft - An Active Highlift Flap. 32nd AIAA Applied Aerodynamics Conference 2014, 1 .

AMA Style

Michael Meyer, Wolfgang Machunze, Matthias Bauer. Towards the Industrial Application of Active Flow Control in Civil Aircraft - An Active Highlift Flap. 32nd AIAA Applied Aerodynamics Conference. 2014; ():1.

Chicago/Turabian Style

Michael Meyer; Wolfgang Machunze; Matthias Bauer. 2014. "Towards the Industrial Application of Active Flow Control in Civil Aircraft - An Active Highlift Flap." 32nd AIAA Applied Aerodynamics Conference , no. : 1.