Installation Effects of a Propeller Mounted on a High-Lift Wing with a Coanda Flap. Part I: Aeroacoustic Experiments

Akkermans, R.A.D.; Pott-Pollenske, Michael; Buchholz, Heino; Delfs, Jan; Almoneit, Daniela

doi:10.2514/6.2014-3191

Cited by 30 publications

(15 citation statements)

References 14 publications

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“…Since then, little literature has been published on propeller-wing interaction both in terms of aerodynamics or aeroacoustics. The two exceptions include Akkermans et al [32] who investigated the noise effect of a tractor propeller on a highlift wing with a Coanda flap. They investigated several angles of attack but only one configuration.…”

Section: Propeller Wake-wing Interactionmentioning

confidence: 99%

Numerical Predictions of Propeller-Wing Interaction Induced Noise in Cruise and Off-Design Conditions

Boots¹

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Using numerical methods, the aeroacoustic field induced by the interaction of a 4-bladed NASA SR-2 propeller and its wake with a wing is investigated under cruise conditions (Mach 0.6). The SmartRotor code, a coupled vortex particle and panel method, which is integrated with an acoustic solver based on the Farassat 1A formulation of the Ffowcs-Williams Hawkings equation, was used. Three main areas were investigated: the effect of propeller tip geometry on the propeller's wake and blade tip vortex; the effect of integrating a wing in the tractor configuration, including the effect of its position, and wing local leading edge sweep; and the effect of operating the combined wing/propeller system in off-design conditions such as low forward speed or in non-axial inflow.It was discovered that tip sweep is effective at reducing propeller tip vortex strength with no adverse effect on noise. Modifying tip dihedral was found to always increase tip vortex strength. Integrating a wing in the wake of the propeller increased the broadband noise generated, but had little effect on harmonic noise. The downstream position of the wing was found to not affect noise while vertical offset from the propeller axis increased noise. The most important discovery was that applying local leading edge sweep to the wing in the region of the propeller's wake decreases noise proportionally to the change in the angle between the helical tip vortex and the wing's leading edge. These noise reductions were on the order of up to 1.3 dB for overall sound pressure level, and 7.5 dB at the blade passage frequency.iii Acknowledgements First on the list of many people to thank must be my supervisor, Professor Daniel Feszty. His constant enthusiasm and support of my work was invaluable whenever simulations weren't working or results seemed less than reasonable. At the same time, his way of providing guidance while allowing me to choose the direction of my research allowed me to follow up on interesting results and truly take ownership of this work. For this and so much more, thank you.

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Section: Propeller Wake-wing Interactionmentioning

confidence: 99%

Numerical Predictions of Propeller-Wing Interaction Induced Noise in Cruise and Off-Design Conditions

Boots¹

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“…15). The results of the acoustic test will be soon published by Akkermans et al [17]. In cooperation with the research project Synergy of Advanced Measurement Techniques for Unsteady and High Reynolds Number Aerodynamic Investigations (SA-MURAI) of the German Aerospace Center (DLR), advanced optical measurement techniques were applied to collect flowfield data and measure propeller blade deformation.…”

Section: Wind-tunnel and Test Conditionsmentioning

confidence: 99%

Aerodynamic Effects of Propeller Slipstream on a Wing with Circulation Control

Beck

Radespiel

Lenfers

et al. 2015

Journal of Aircraft

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The German Bürgernahes Flugzeug (Citizen-Oriented Airplane) research program advances technologies for high-lift systems using circulation control Coandă-type flaps. The interaction of these high-lift systems with a propeller engine is the subject of the present work. A large and complex wind-tunnel model equipped with an active high-lift system and a powered propeller was designed, manufactured and instrumented. The wind-tunnel data show the potentials of the active high-lift system in three-dimensional wing applications. The results characterize and quantify the interactions between a propeller and a high-lift wing by using systematic variations of blowing momentum and propeller thrust. The results represent a unique database for future efforts to improve the efficiency of active lift and for validation of numerical simulation methods.

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“…The test system of contra-rotating fan is shown 2 Mathematical Problems in Engineering (2) (1) Air in Figure 1: Experiment schematic of the contra-rotating fan.…”

Section: Methodsmentioning

confidence: 99%

“…Because of the large numbers of such devices and their role in mining industry, the noise generated by running contra-rotating fans should be reduced to improve comfortable working environments and human life quality. The installation effects of impellers were important as they can significantly alter the sound radiation as compared to an isolated propeller [2]. Meanwhile, the axial spacing was an important factor which can affect the aerodynamic performance of contra-rotating fan.…”

Section: Introductionmentioning

confidence: 99%

The Acoustical Behavior of Contra-Rotating Fan

Kou

Liu

2018

Mathematical Problems in Engineering

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The noise produced by a contra-rotating ventilator can cause injury to humans. Therefore, it is important to reduce noise caused by ventilators. In this study, the Ffowcs Williams and Hawkings (FW-H) model was used to simulate the acoustics of four different axial impeller spacing points based on the unsteady flow field through a FBD No. 8.0 contra-rotating ventilator. Experiments were conducted to verify the correctness of the numerical model. Meanwhile, the Variable Frequency Drive (VFD) drives the two motors of 55 kW to give the impellers different speeds to distinguish different conditions. The results showed that the main noise source of the ventilator was the two rotating impellers and the area between them. For the same axial space, the noise decreased with the increase of flow rate and then decreased. And the amplitude of the discrete pulse increased gradually. It can be concluded that the vortex acoustics decreased gradually with the increase of flow rate and the rotating acoustics were the major contributor. With the axial distance increasing, the noise caused by the two impellers was weak, and the frequencies of sound pressure level moved toward medium-and low-frequency bands gradually. The suitable axial space could reduce noise and improve the working environment.

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Installation Effects of a Propeller Mounted on a High-Lift Wing with a Coanda Flap. Part I: Aeroacoustic Experiments

Cited by 30 publications

References 14 publications

Numerical Predictions of Propeller-Wing Interaction Induced Noise in Cruise and Off-Design Conditions

Numerical Predictions of Propeller-Wing Interaction Induced Noise in Cruise and Off-Design Conditions

Aerodynamic Effects of Propeller Slipstream on a Wing with Circulation Control

The Acoustical Behavior of Contra-Rotating Fan

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