A New Actuator Disk Model for the TAU Code and Application to a Sailplaine with a Folding Engine

Raichle, Axel; Melber-Wilkending, Stefan; Himisch, Jan

doi:10.1007/978-3-540-74460-3_7

Cited by 16 publications

(6 citation statements)

References 1 publication

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“…Turbulence was modeled by the Spalart-Allmaras one-equation formulation. The active actuator disk model uses blade element theory to calculate the steady forces applied to the fluid [21]. This means that the actual inflow is taken into account which is particularly important for installed propellers.…”

Section: Integrated Propeller For Noise Shieldingmentioning

confidence: 99%

SFB 880: aeroacoustic research for low noise take-off and landing

Delfs¹,

Faßmann²,

Lippitz

et al. 2014

CEAS Aeronaut J

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This paper gives an overview about prediction capabilities and the development of noise reduction technologies appropriate to reduce high lift noise and propeller noise radiation for future low noise transport aircraft with short takeoff and landing capabilities. The work is embedded in the collaborative research centre SFB 880 in Braunschweig, Germany. Results are presented from all the acoustics related projects of SFB 880 which cover the aeroacoustic simulation of the effect of flow permeable materials, the characterization, development, manufacturing and operation of (porous) materials especially tailored to aeroacoustics, new propeller arrangements for minimum exterior noise due to acoustic shielding as well as the prediction of vibration excitation of aircraft structures, reduced by porous materials.

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Section: Integrated Propeller For Noise Shieldingmentioning

confidence: 99%

SFB 880: aeroacoustic research for low noise take-off and landing

Delfs¹,

Faßmann²,

Lippitz

et al. 2014

CEAS Aeronaut J

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show abstract

“…This enables the embedding into the finite volume discretization of the cell-vertex based flow solver. Further details concerning the implementation of the method can be found in [12] and [13]. Applications of the TAU AD model for propeller aircraft configurations are described in [14][15][16].…”

Section: Tau Rans Actuator Disk Methodologymentioning

confidence: 99%

A Blade Element Theory Based Actuator Disk Methodology for Modeling of Fan Engines in RANS Simulations

Spinner

Keller

Schnell

et al. 2020

Aiaa Aviation 2020 Forum

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A modified actuator disk method based on blade element momentum theory is applied to an UHBR turbofan engine with the DLR TAU Code. The method is compared against RANS simulations with a common thermodynamic engine boundary condition and high-fidelity 360°u RANS simulations as well as RANS mixing-plane data from the design process of the engine conducted with the DLR flow solver TRACE. The input data of the actuator disk model comprise sectional lift and drag coefficients of the rotor and stator blades which are obtained by 2D RANS computations of the blade sections performed with the TAU Code. The boundary conditions for these 2D computations are derived from the aforementioned RANS mixing-plane results obtained during the design process of the investigated engine.Good agreement between the RANS actuator disk method and the uRANS results as well as the RANS mixing-plane data is observed. The actuator disk model is able to predict global engine performance data for different engine operating points. Detailed analysis shows that the actuator disk model is able to reproduce characteristic non-uniform inflow phenomena that could in the past only be modeled with uRANS computations. Additionally the model is capable to accurately predict the thrust distribution between rotor and stator. Therefore it is able to fill the gap between the currently used thermodynamic engine boundary condition and high-fidelity uRANS computations with only a minor increase in required computational resources.

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“…In order to model the turboprop engines, actuator disks based on the 2D blade element theory are implemented. In this way, the local load of the propellers is calculated based on a given radial distribution of force coefficients along the blades and the local flow conditions [16].…”

Section: Methodsmentioning

confidence: 99%

Numerical investigations of aerodynamic properties of a propeller blown circulation control system on a high wing aircraft

Keller

Rudnik

2016

CEAS Aeronaut J

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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 in order 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 takeoff 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. Additionally, 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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A New Actuator Disk Model for the TAU Code and Application to a Sailplaine with a Folding Engine

Cited by 16 publications

References 1 publication

SFB 880: aeroacoustic research for low noise take-off and landing

SFB 880: aeroacoustic research for low noise take-off and landing

A Blade Element Theory Based Actuator Disk Methodology for Modeling of Fan Engines in RANS Simulations

Numerical investigations of aerodynamic properties of a propeller blown circulation control system on a high wing aircraft

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