Validation of Actuator Disk Simulations of CROR Propulsion Systems at Low-Speed Flight Conditions

Gutierrez, Carlos Omar Marquez; Stürmer, Arne; Clemen, Carsten; Grimminger, Andreas

doi:10.2514/6.2012-2787

Cited by 11 publications

(7 citation statements)

References 10 publications

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“…However, the use of an actuator disk model can greatly reduce computational costs due to the minimization of the mesh size and the use of steady simulations, while main aspects of the propeller impact such as an inhomogeneous change of the flow momentum and swirl are considered. The procedure already showed robust behavior and good results in various applications such as the simulation of a contra-rotating open rotor [17] and a circulation controlled high-lift wing-propeller configuration, which is similar to the underlying configuration [18].…”

Section: Methodsmentioning

confidence: 95%

“…Since the stall occurs due to a separation in the upwash region of the propeller, the maximum angle of attack is certainly dependent on the accuracy of the actuator disk model. However, comparisons of simulations with actuator disk model with wind-tunnel tests delivered good results, especially regarding the flow conditions behind the Propeller [17,18].…”

Section: Stall Behaviormentioning

confidence: 99%

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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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Section: Methodsmentioning

confidence: 95%

Section: Stall Behaviormentioning

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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“…Detailed information on the actuator disk implementation can be found in [14,15]. The actuator disk model has shown robust behavior and good results in terms of performance parameters ( C T ,C P ) as well as slipstream velocity distributions (axial and circumferential) for various applications such as the simulations of conventional propellers [16], contra-rotating open rotors [17], and more recently turbofans [18].…”

Section: Methodsmentioning

confidence: 99%

Towards higher aerodynamic efficiency of propeller-driven aircraft with distributed propulsion

Keller

2021

CEAS Aeronaut J

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The scope of the present paper is to assess the potential of distributed propulsion for a regional aircraft regarding aero-propulsive efficiency. Several sensitivities such as the effect of wingtip propellers, thrust distribution, and shape modifications are investigated based on a configuration with 12 propulsors. Furthermore, an initial assessment of the high-lift performance is undertaken in order to estimate potential wing sizing effects. The performance of the main wing and the propellers are thereby equally considered with the required power being the overall performance indicator. The results indicate that distributed propulsion is not necessarily beneficial regarding the aero-propulsive efficiency in cruise flight. However, the use of wing tip propellers, optimization of the thrust distribution, and wing resizing effects lead to a reduction in required propulsive power by $$-2.9$$ - 2.9 to $$-3.3\,\%$$ - 3.3 % compared to a configuration with two propulsors. Adapting the leading edge to the local flow conditions did not show any substantial improvement in cruise configuration to date.

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“…Fig. 4b shows the unstructered mesh for the calculations using the DLR TAU code [8]. The single blade loading function, cf.…”

Section: Rolls-royce Rig 145 -1/6th-scale Crormentioning

confidence: 99%

“…The front rotor, however, is influenced only by small potential perturbations induced upstream by the rear rotor.a) Uninstalled counter rotating open rotor at the DNW test facility. From [7] b) CFD Mesh for the URANS simulation of the CROR.From[8] …”

mentioning

confidence: 99%

Validation of a Model for Open Rotor Noise Predictions and Calculation of Shielding Effects using a Fast BEM

Lummer

Richter

Pröber

et al. 2013

19th AIAA/CEAS Aeroacoustics Conference

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For application in BEM/FMM shielding calculations a simple analytical model for the loading noise of contra rotating open rotors (CRORs) with different rotational speeds is derived. Following previous work of S.L.A. Glegg, the model is formulated in frequency domain and the pressure is approximated by a set of dipoles on circles on the propeller disk. The dipole strength depends on the blade loading function and can be obtained, e.g., by CFD calculations. For arbitrary rotational speeds, the blade loading function is not a perodic function on the propeller disk anymore and must be approximated, e.g., by a least-squares Fourier approximation. The CROR model is checked against a time domain solution using rotating dipoles and validated with data from a test of Rolls-Royce's open rotor model rig 145 in DNW. The lowest three and most dominant peaks in the spectrum of the uninstalled rotor are well predicted by the method with errors less than 3dB with a correct directivity. For higher frequencies larger errors are observed. The CROR model has been developed for shielding calculations with the DLR BEM/FMM code. Some information about the code is given and the applicability of the model is demonstrated for a CROR installed at a modified DLR F6 aircraft geometry.

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Validation of Actuator Disk Simulations of CROR Propulsion Systems at Low-Speed Flight Conditions

Cited by 11 publications

References 10 publications

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

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

Towards higher aerodynamic efficiency of propeller-driven aircraft with distributed propulsion

Validation of a Model for Open Rotor Noise Predictions and Calculation of Shielding Effects using a Fast BEM

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