Lutz Taubert

Interests

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Courses

Scholarly Contributions

Chapters

• Taubert, L., & Wygnanski, I. (2009).

  Preliminary Experiments Applying Active Flow Control to a 1/24th Scale Model of a Semi-Trailer Truck

  . In Lecture Notes in Applied and Computational Mechanics, The Aerodynamics of Heavy Vehicles II: Trucks, Buses, and Trains. Springer. doi:10.1007/978-3-540-85070-0_9

Journals/Publications

• Taubert, L., Kay, G., Wygnanski, I., & Ol, M. (2023). Proposed active flow control enabled hybrid tilt propeller/tilt wing aircraft. International Journal of Numerical Methods for Heat and Fluid Flow, 33(4). doi:10.1108/hff-11-2022-0653
  More info

  Purpose: This paper aims to address shortcomings of current tiltrotor designs, such as the small aspect ratio of the wings, large download and the close proximity of the rotor tips. It also aims to avoid the complex transition of tiltrotors to normal airplane mode. Design/methodology/approach: This design combines tiltrotor and tiltwing aircraft designs into a hybrid that is augmented by active flow control, using a gimbaled channel wing for attitude control in hover. Findings: The proposed hybrid design is based on experimental results of components that were tested individually for potential use in hover and steep ascend from a stationary position. Originality/value: This research was inspired by the extremely short take-off of the V-22, when its rotors were tilted forward. It combines several design approaches in a unique way to achieve extremely short take-off capabilities combined with high-speed and reduced maintenance costs.
• Veismann, M., Gharib, M., Taubert, L., & Wygnanski, I. (2023). Effect of Leading-Edge Cranks on Stability and Control of Active-Flow-Control-Enabled Tailless Aircraft. AIAA Journal, 61(9). doi:10.2514/1.j062561
  More info

  The Swept Wing Flow Test (SWIFT) is a tailless unmanned combat aerial vehicle (UCAV) model to be tested at high Reynolds numbers in NASA’s National Transonic Facility. The model is designed around a A-shaped wing with a single, large crank at its leading edge (LE). It suffers from an unstable nose-up pitch departure resulting from flow separation augmented by the LE crank. A small-scale, modular wind tunnel model (Re ≈ 106) was built that allowed for changes in the crank angle by increasing the outboard wing sweep. Eliminating the crank entirely increased the CL,max and changed the sign of pitch departure, thus exposing the significance of the LE crank. The model was equipped with sweeping jet actuators that could be individually enabled by valves located at the actuator inlets, allowing one to explore the role of active flow control (AFC) in expanding the model’s longitudinal stability margins and controlling its yaw while being cognizant of the coupling between changes in the model’s planform and their effect on AFC. Test results indicated that selective actuation depending on the model’s attitude modified the flow and dramatically increased the trimmed CL, while further suggesting that the actuation should dynamically change with incidence to improve AFC efficacy.
• Craig, S. A., Taubert, L., Padilla, V. E., & Bearden, K. P. (2022). Calibration and performance characterization of a Mach 5 Ludwieg tube. Review of Scientific Instruments, 93(8). doi:10.1063/5.0093052
• Taubert, L., Bearden, K. P., Padilla, V. E., & Craig, S. A. (2022). Calibration and performance characterization of a Mach 5 Ludwieg tube. Review of Scientific Instruments, 93(8), 085104. doi:10.1063/5.0093052
• Chen, J., Kalyankar, H. B., Kay, G., Phillips, E. J., Taubert, L., & Wygnanski, I. (2020).

  Drag reduction experiments on a wing at incidence angles appropriate to combined tilt-rotor & tilt-wing configurations in hover

  . 60th Israel Annual Conference on Aerospace Sciences, IACAS 2020.
• Wygnanski, I., Taubert, L., & Jentzsch, M. (2019). Using Sweeping Jets to Trim and Control a Tailless Aircraft Model. AIAA Journal, 57(6), 2322-2334. doi:10.2514/1.j056962
• Taubert, L., Tewes, P., & Wygnanski, I. (2014). Applying the Boundary-Layer Independence Principle to Turbulent Flows. Journal of Aircraft, 51(1), 175-182. doi:10.2514/1.c032206
• Doty, M. J., Lucas, N. J., Taubert, L., & Wygnanski, I. (2013).

  Reducing the noise emanating from a twin jet nozzle using flexible filaments

  . Experiments in Fluids. doi:10.1007/s00348-013-1504-8
• Suehiro, E., Taubert, L., & Wygnanski, I. (2012).

  The mixing layer downstream of a ``$\Lambda$''-notched splitter plate

  . Bulletin of the American Physical Society.
• Chen, C., Kurz, H. B., Taubert, L., Tewes, P., & Wygnanski, I. (2011).

  The application of boundary layer independence principle to three-dimensional turbulent mixing layers

  . Journal of Fluid Mechanics. doi:10.1017/jfm.2011.95
• Taubert, L. (2010).

  On the Wake of an Inclined Circular Cylinder

  . Dissertation, Technical University of Berlin. doi:10.14279/depositonce-2394
• Calkins, F. T., Mabe, J. H., Taubert, L., Wesley, B., Woszidlo, R., & Wygnanski, I. (2009).

  Single Dielectric Barrier Discharge Plasma Actuators for Improved Airfoil Performance

  . Journal of Aircraft. doi:10.2514/1.37638
  More info

  The applicability of single dialectic barrier discharge plasma actuators for use as active flow control devices, capable of enhancing the performance of airfoils, was assessed in this investigation. Measurements were carried out on two thick airfoils with simple flaps: a NACA0021 and an airfoil that is similar to those commonly used on tiltrotor aircraft. The chord length of the airfoils was approximately 0.3 and 0.25 m, respectively, and the span was approximately 0.6 m. They were both tested in the same wind tunnel with a test section of 0.6 x 1.1 m. Freestream velocities varying from 5 to 15 m/s were tested, corresponding to chord Reynolds numbers ranging between 0.8 × 10 5 and 3 × 10 5 . The lift, moment, and form drag were obtained from the pressure distributions over the airfoil's surface, and the total drag was calculated from a wake survey. The range of incidence angles α varied from ―4deg
• Wygnanski, I., Taubert, L., & Woszidlo, R. (2009). Manipulating the Flow over Spherical Protuberance in a Turbulent Boundary Layer. AIAA Journal, 47(2), 437-450. doi:10.2514/1.39930
• Calkins, F. T., Mabe, J. H., Taubert, L., Wesley, B., Woszidlo, R., & Wygnanski, I. (2007).

  On the Use of Single Dielectric Barrier Discharge Plasma Actuators for Improving the Performance of Airfoils

  . 37th AIAA Fluid Dynamics Conference.
  More info

  The applicability of Single Dialectic Barrier Discharge (SDBD) plasma actuators for use as active flow control devices, capable of enhancing the performance of airfoils, was assessed in this investigation. Measurements were carried out on two thick airfoils with simple flaps, a NACA0021 and an airfoil similar to those commonly used on tilt-rotor aircraft. The chord length of the airfoils was approximately 0.3 and 0.25 meters respectively and the span was approximately 0.6 meters. They were both tested in the same wind tunnel with a test section of 0.6 meters x 1.1 meters. Free-stream velocities varying from 5 m/s to 15 m/s were tested, corresponding approximately to chord Reynolds numbers ranging between 0.8x10 5 & 3x10 5 . The lift, moment and form drag were obtained from the pressure distributions over the airfoil’s surface while the total drag was calculated from a wake survey. The range of incidence angles, α, varied from –4 o < α < +20 o and flap deflections, δf, of 0 o and 15 o were tested. The location of the actuation was also altered. Two data sets are presented: one where the actuator was placed at approximately 5% of the chord and the other where it was located just upstream of the flap shoulder at a chord location corresponding to about 75%. The momentum input of the SDBD plasma actuators was measured with a hot wire and was in good agreement with previously published results. The input momentum is very weak and is not sufficient to prevent separation at Reynolds numbers greater than 100,000. The SDBD plasma actuators used in this study may only provide sufficient momentum to be effective at very low Reynolds numbers, such as those appropriate to micro-air-vehicles. Under special circumstances their passive presence on the surface may trip the boundary layer making it more resistant to separation, but in those cases a proper roughness strip or vortex generators may delay separation more effectively.
• Taubert, L., & Wygnanski, I. (2005).

  Controlling the Flow around a Swept Back Circular Cylinder Using Periodic Excitation

  . Bulletin of the American Physical Society.
• Kjellgren, P., Taubert, L., & Wygnanski, I. (2001).

  Finite Elemente Large Eddy Simulation of Flows Past Bluff Bodies with Active Flow Control

  . APS Division of Fluid Dynamics Meeting Abstracts.
• Taubert, L., & Wygnanski, I. (2001).

  On Controlling Separation and Vortex Shedding from a Circular Cylinder

  . APS.

Proceedings Publications

• Kalyankar, H. B., Urreixtieta, U., Higuera Pierre Noel, A., Taubert, L., & Wygnanski, I. J. (2026, 12-16 January).

  On the Interaction Between a Jet and a Vortex on a Lambda Wing

  . In AIAA SciTech Forum, Orlando, FL, USA.
• Vibhu, M., Taubert, L., & Wygnanski, I. J. (2026, 12-16 January).

  On the Use of Coanda Effect on Truncated Airfoils, or The Jet-Flap Issues Revisited

  . In AIAA SciTech Forum, Orlando, FL, USA,.
• Kalyankar, H., Noel, A. H., Urreiztieta, U., Taubert, L., & Wygnanski, I. (2025). On Controlling the Path & Structure of a Leading-Edge Vortex by a Single, Small Jet. In AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2025.
  More info

  The flow over a straight and a cranked lambda wing planform having a flat upper surface, and a sharp leading edge was investigated experimentally, using flow visualization and particle image velocimetry, while measuring the forces and moments on the model. A single steady jet located just inboard of the crank provided the wing with nose up or down pitch control authority and enabled the wing to be trimmed at high angles of incidence. To achieve this result the jet was rotated at various angles relative to the oncoming free stream therefore disrupting the feedback mechanism existing between the primary leading-edge vortex and the separated shear layer that feeds it with vorticity. In the absence of a crank, this feedback is provided by the vortical layer (secondary vortex) that is forced upward by the primary vortex and is entrained into the separated shear layer. In the presence of the crank, a new vortex created downstream of a crank serves a similar purpose as the shear layer. The experiments were carried out in a low-speed wind tunnel at 25 meters/second therefore providing a Reynold number of approximately 1.2 x 106 and a Mach number smaller than 0.1.
• Kalyankar, H., Urreiztieta, U., Pierre Noel, A. H., Taubert, L., & Wygnanski, I. (2025). On the Informed Flow Control Over a Blended-Wing-Body Model and its Simple Surrogate of Identical Planform. In AIAA AVIATION FORUM AND ASCEND, 2025.
  More info

  Tests were carried out in a university-scale atmospheric wind tunnel on a NATO designed Swept Wing Flow Test (SWiFT) model at incompressible Mach numbers and Reynolds numbers (Re) ranging from Re=0.2 x 106to Re= 2 x 106. The initial purpose was to compare results with those from the National Transonic Facility (NTF) to assess the significance of Re. After comparing the force balance data of the two tests and seeing that an increase in Re did not result in novel phenomena, the evolution of the Leading-Edge Vortex (LEV) and its lift-off from the surface due to the LE crank was investigated. Based on this information, a single small jet was chosen to alter the forces and moments acting on this model and provide information about the interaction between the small jet and the LEV. Preliminary results indicate that the location and orientation of a jet actuator are as important as the jet momentum, therefore requiring optimization for different parts of the flight envelope. To ascertain the significance of the crank angle and its location on the wing relative to other design parameters, a simplified flat-top lambda wing planform with a sharp leading edge was tested at Re= 1.2 x 106. Oil flow visualization exposed the differences between these two models that were exposed by probing the LEV by Particle Image Velocimetry (PIV). The use of PIV revealed extremely large periodic oscillations in the flow that were associated with localized separation and vortex lift-off, providing a reason for flutter. These oscillations were observed on both models, and they were attributed mostly to the crank. Consequently, a substantial reduction of these oscillations became an added task for the useful application of Active Flow Control (AFC).
• Kalyankar, H., Pompe, J., Taubert, L., & Wygnanski, I. (2024, July-August). On the Use of Discrete Jets for Control of Moments on Tailless Aircraft. In AIAA Aviation Forum and Ascend.
  More info

  The broad practical purpose of this study was to explore the effectiveness of Active Flow Control (AFC) in controlling a tailless aircraft model called the SWIFT that was designed in the UK under the auspices of NATO’s Advanced Vehicle Technology program. Wind tunnel tests focused on the maintenance of trim at high lift coefficients using a single supersonic jet emanating from a small nozzle at an appropriate location and orientation relative to the free stream. Although none of the AFC parameters was properly optimized the trimmed lift coefficient was tripled. To understand the effect of AFC on the flow over such a wing, flow visualization and Particle Image Velocimetry (PIV) were used. Proper Orthogonal Decomposition applied to this data revealed unsteady behavior in the vortex lift-off and its advection over the outer wing that was effectively subdued by AFC thus extending the range of incidence angles that could be flown. Preliminary tests were carried out on yawing and rolling moments exploring the possibility of replacing conventional control surfaces on an airplane by AFC. Wind tunnel data were acquired at Reynolds number of 1.6x106 based on the root chord of the semi-span model used.
• Kalyankar, H., Taubert, L., & Wygnanski, I. (2024, March). On the Control of a Leading-Edge Vortex & its Liftoff on a Cranked, Swept Back Wing. In 58th 3AF International Conference on Applied Aerodynamics.
  More info

  This study examines flow over a cranked {\lambda}-wing model with a sweep of {\Lambda}=60{\deg} of the inboard leading edge (LE) that changed to {\Lambda}=30{\deg} outboard of the crank. The study focuses on the liftoff of the inboard Leading-Edge Vortex (LEV) and its influence over the flow on the outer wing. Stereoscopic Particle Image Velocimetry (SPIV) indicates that the flow is largely separated and dominated by strong outboard spanwise flow at {\alpha}=14{\deg}. The separation is mitigated by a small, steady supersonic jet that interacted with the lifted vortex and changed the pitch characteristic of the entire model. The use of Proper Orthogonal Decomposition (POD) revealed the unsteadiness of the separated structures that may cause wing flutter.
• Craig, S. A., Taubert, L., Bearden, K. P., & Padilla, V. E. (2021). Calibration of a Mach 5 Ludwieg tube at the University of Arizona. In AIAA AVIATION 2021 FORUM.
• Wygnanski, I. J., Kay, G. A., & Taubert, L. (2021). On the Hybrid Tilt-Wing, Tilt Propeller, Active Flow Control Enabled Runway Independent Airplane.. In AIAA AVIATION 2021 FORUM.
• Taubert, L., Craig, S. A., & Flood, J. T. (2020). Correction: Flow quality mapping of the Mach 4 Quiet Ludwieg Tube. In AIAA Scitech 2020 Forum.
• Taubert, L., Flood, J. T., & Craig, S. A. (2020). First and Mack-mode instabilities in a flat-plate boundary layer at Mach 4. In AIAA Scitech 2020 Forum.
• Craig, S. A., Taubert, L., & Flood, J. T. (2019). Initial Flow Quality of the Mach 4 Quiet Ludwieg Tube. In AIAA Aviation 2019 Forum.
• Kalyankar, H. B., Taubert, L., & Wygnanski, I. J. (2019). Control of turbulent separation from an inclined cylinder of finite aspect ratio, thus affecting its yaw. In 59th Israel Annual Conference on Aerospace Sciences.
• Taubert, L., Wygnanski, I. J., Phillips, E., & Menge, P. M. (2019). Passive and Active Leading Edge devices on a simple swept back wing. In AIAA Aviation 2019 Forum.
• Wygnanski, I. J., Taubert, L., Phillips, E., Jentzsch, M. P., Menge, P. M., & Forster, M. (2019). On the Use of Active Flow Control to Change the Spanwise Flow on Tailless Aircraft Models, Thus Affecting their Trim and Control. In 8th AIAA Flow Control Conference.
• Taubert, L., Kalyankar, H. B., & Wygnanski, I. J. (2018). Re-orienting the Turbulent flow over an Inclined Cylinder of Finite Aspect ratio. In 2018 Flow Control Conference.
• Wygnanski, I. J., Taubert, L., & Jentzsch, M. P. (2017). On the Use of Sweeping Jets to Trim and Control a Tailless Aircraft Model. In 35th AIAA Applied Aerodynamics Conference.
• Wygnanski, I. J., Taubert, L., & Jentzsch, M. P. (2016). Active Flow Control on the Stability and Control Configuration (SACCON). In 8th AIAA Flow Control Conference.
• Wygnanski, I. J., Taubert, L., Little, J. C., Endrikat, S., Roentsch, B., Farbos de Luzan, C., & Gutmark, E. J. (2016). Physics and Control of the Flow over a Generic Trapezoidal Wing Planform. In 54th AIAA Aerospace Sciences Meeting / AIAA SciTech Forum.
• Taubert, L., & Tewes, P. (2015). Control of Separation on a Swept Wing using Fluidic Oscillators. In AIAA SCITECH 2022 Forum.
• Wygnanski, I. J., Taubert, L., & Tewes, P. (2014). On the Effect of Sweep on Separation Control. In 7th AIAA Flow Control Conference.
• Wygnanski, I. J., Taubert, L., Suehiro, E., & Zalewski, N. (2014). On Controlling the Flow in a Mixing Layer Downstream of a "Lambda" Notch. In 7th AIAA Flow Control Conference.
• Taubert, L., Tewes, P., Wygnanski, I., & Zalewski, N. (2012).

  On the Applicability of the Boundary Layer Independence Principle to Free and Bounded Turbulent Flows in Absence of Pressure Gradient

  . In 7th International Symposium on Turbulence Heat and Mass Transfer.
• Wygnanski, I., Taubert, L., Seele, R., Graff, E., Gharib, M., & Lin, J. (2012). Improving Rudder Effectiveness with Sweeping Jet Actuators. In 6th AIAA Flow Control Conference.
• Taubert, L., Strangfeld, C., Nayeri, C., & Paschereit, C. (2011). Parametric Investigations of the Leading Edge Vortex on a Delta Wing. In 41st AIAA Fluid Dynamics Conference and Exhibit.
• Wygnanski, I., Taubert, L., & Tewes, P. (2010). On the Use of Sweeping Jets to Augment the Lift of a Lambda-Wing. In 28th AIAA Applied Aerodynamics Conference.
• Wygnanski, I., Taubert, L., Lucas, N., Woszidlo, R., & McVeigh, M. (2008). Discrete Sweeping Jets as Tools for Separation Control. In 4th AIAA Flow Control Conference.
• Wygnanski, I., Taubert, L., Mabe, J., Calkings, F., Wesley, B., & Woszidlo, R. (2007). On the use of plasma actuators for improving the performance of airfoils. In 37th AIAA Fluid Dynamics Conference and Exhibit.
• Wygnanski, I., & Taubert, L. (2006). Investigation of the Near Wake of a Swept Back Cylinder with Forcing. In 3rd AIAA Flow Control Conference.
• Wygnanski, I., & Taubert, L. (2004). Control of Vortex Shedding from a Cylinder at Different Sweep Back Angles. In 2nd AIAA Flow Control Conference.
• Wygnanski, I., Taubert, L., & Kjellgren, P. (2002). Generic Bluff Bodies with Undetermined Separation Location. In AIAA 1st Flow Control Conference.

Presentations

• Taubert, L., Kay, G., & Wygnanski, I. J. (2022, March). Proposed Active Flow Control Enabled Hybrid Tilt Propeller / Tilt Wing Aircraft. 3AF International Conference on Applied Aerodynamics. Toulouse, France.