Experimental validation of a lifting surface theory for rotor-stator interaction noise generation

Sijtsma, Pieter; Rademaker, E.R.; Schulten, J.B.H.M.

doi:10.2514/6.1996-1744

Cited by 4 publications

(4 citation statements)

References 5 publications

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“…This method was validated by several wind tunnel experiments in the period 1987 through 1995. A good agreement was found between theory and measurements 8,9 . Furthermore, the method was compared to another lifting surface method 5 in the 3rd CAA Workshop 10 .…”

Section: Introductionsupporting

confidence: 73%

Wake Modelling Accuracy Requirements for Prediction of Rotor Wake-Stator Interaction Noise

Sijtsma

Schulten²

2003

9th AIAA/CEAS Aeroacoustics Conference and Exhibit

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Rotor wake-stator interaction is an important element of aircraft engine noise, especially in the rear arc. For numerical predictions of this type of engine noise, an accurate rotor wake description is indispensable. However, for most CFD codes accurate calculation of the development of turbulent rotor wakes is not something natural. To assess the importance of wake modelling accuracy, the NLR lifting surface model was used for a parametric study. Many rotor wake-stator interaction calculations were made on a configuration with realistic dimensions. Systematic variations of wake depth, wake width, and axial and circumferential position of the wake origin were carried out. It was found that for 1 dB precision in the final acoustic result these parameters must have a relative accuracy varying from 6% to 12%. This is a real trial of strength for most CFD models. With the same 1 dB precision requirement, it was found that relative errors in the prediction of rotor viscous drag, which is an important factor in the wake development, are acceptable up to 23%.

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Section: Introductionsupporting

confidence: 73%

Wake Modelling Accuracy Requirements for Prediction of Rotor Wake-Stator Interaction Noise

Sijtsma

Schulten²

2003

9th AIAA/CEAS Aeroacoustics Conference and Exhibit

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“…Sijtsma, Rademaker, and Schulten (Ref. 41) also reported that reflections from the inlet and nozzle can be significant over a wide range of speeds and should be included in fan noise predictions. Schulten's method (Ref.…”

Section: Nasa/tm-97-206533mentioning

confidence: 94%

Fan noise prediction - Status and needs

Huff

1998

36th AIAA Aerospace Sciences Meeting and Exhibit

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“…Several numerical methods have been developed in order to study wake or potential flow field interaction of adjacent cascades. Semi-analytic methods, like the lifting surface theory are fast tools for 2D or 3D investigations, if axial main flow is uniform and the stator vanes are thin and aligned with the main flow, [28][29][30][31]. Time linearized Euler codes are very popular methods as they allow to investigate radially varying and swirling flow [5,6,9,26].…”

Section: Introductionmentioning

confidence: 99%