Issue 
Acta Acust.
Volume 6, 2022
Topical Issue  Aeroacoustics: state of art and future trends



Article Number  27  
Number of page(s)  8  
DOI  https://doi.org/10.1051/aacus/2022022  
Published online  04 July 2022 
Scientific Article
Shielding of rotor noise by plates and wings
Department of Mechanical Engineering, University of Bath, Bath BA2 7AY, United Kingdom
^{*} Corresponding author: m.j.carley@bath.ac.uk
Received:
28
February
2022
Accepted:
8
June
2022
A method of noise reduction proposed for the next generation of aircraft is to shield noise from the propulsion system, by positioning the noise source over a wing or another surface. In this paper, an approximate analysis is developed for the acoustic field far from a circular source placed near the edge of a semiinfinite plate, a model problem for shielding of noise by a wing and for scattering by a trailing edge. The approximation is developed for a source of small radius and is found to be accurate when compared to full numerical evaluation of the field.
Key words: Noise shielding / Rotor noise / Trailing edge / Scattering
© The Author(s), Published by EDP Sciences, 2022
This is an Open Access article distributed under the terms of the Creative Commons Attribution License (https://creativecommons.org/licenses/by/4.0), which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
1 Introduction
The effect of airframe configurations on the propagation of noise from propulsion systems is a question which has been studied over a number of years. In particular, studies have been conducted of the possibility of positioning propulsion systems in such a way that the airframe acts to “shield” the noise source and reduce noise levels reaching the ground. One example is the “Silent Aircraft” Initiative, in which a study was conducted of the scattering of noise from sources placed above the blended wing body configuration [1]. Another study [2] examined the effect of propeller positioning on an otherwise conventional airframe, making use of the tailplane for acoustic shielding. As electric propulsion improves, and novel configurations using airframe shielding for noise reduction become more feasible, there is a greater need for reliable methods which can be used in design and to provide insight into the propagation of sound around airframes.
The literature on the use of aircraft configurations to shield noise from propulsion systems is not as extensive as that on the reduction of noise at source, and has tended to concentrate on reducing environmental noise from jet and turbofan systems. Czech and Thomas [3] note that there have been very few studies on the installation effect on open rotors of airframe elements other than pylons. They report experimental studies of noise from an open rotor system on a conventional and on a hybrid wing body airframe, as part of an extensive study on installation and shielding effects [4–6]. The airframe configuration used in these tests had a swept trailing edge and so was not comparable to the model problem considered in this paper, but it did demonstrate shielding effects of up to 12 dB for certain axial displacements of the rotor [3].
The prediction of shielding effects on propulsion noise appears to have been carried out mainly using numerical approaches such as the use of computational fluid dynamics (CFD) data in a permeable surface integration method [7] or a boundary element method (BEM) calculation using a suitable model for the rotor source [8]. A comparison of shielding patterns from BEM predictions and experimental data has also shown good agreement in the case of a monopole point source [9] and gives confidence that the BEM is a suitable method for assessment of shielding when sufficient information about the aircraft configuration is available.
There does not appear to be a reliable method in the literature for approximate prediction of shielding effects. In a study of shielding of noise from a counterrotation open rotor [10], two theories for shielding attenuation, barrier theory and halfplane diffraction, were compared to experimental data, approximating the rotor by a point source. It was found that neither gave accurate results, overpredicting the attenuation by 5 dB when the point source approximation was used. The error may have been increased by the source having a higher frequency than was used in developing the curve fits used in the barrier theory approximations [11].
The theory for shielding by a wing is based on the problem of diffraction by a semiinfinite plane, first addressed more than a century ago [12]. A comprehensive review of the theory of noise shielding [13] discusses in some depth the analysis of noise from point sources near shielding bodies and the different approximations which apply throughout the field. In particular, the applicability and breakdown of the geometric acoustics approximation is considered, as well as the existence of “shadow” zones around a shielding body, regions in which the source is not “visible”, being blocked by the body. In this paper, the theory to be applied will be the standard analysis of scattering by a semiinfinite plate, extended to include the effects of a mean flow [14].
The motivation for the work in this paper is then the lack of a reliable model for shielding of noise from rotating sources in aeronautical applications. We present an analysis of farfield noise from a rotating source which replaces the point source approximation with the models normally used in established theory for noise from rotating sources. The result is an approximation which compares well to full numerical solution and should be useful to designers and researchers as a starting point for parametric studies of rotor positioning in new configurations.
2 Analysis
The problem of scattering by a plane is an old one [12, 13], which has been extended to include the effect of mean flow in the acoustic case [14]. We begin by presenting existing results for the problem in a form which are then incorporated into standard methods for the calculation of the acoustic far field of rotating sources.
2.1 Green’s function
The coordinate system used to analyze the scattering of sound by a semiinfinite plate is shown in Figure 1. A uniform flow of Mach number M_{0} is imposed normal to the trailing edge. A Cartesian coordinate system (x, y, z) is centred on the edge of the plate, with x parallel to the flow, y normal to the plate and z aligned with the edge. A cylindrical coordinate system (r, θ, z) is defined, with and θ = tan^{−1} y/x. The Green’s function for the field at a point (x, y, z) due to a source of time dependence exp[−iωt] at (x_{0}, y_{0}, z_{0}) is given by [14],(1)(2)where is the Hankel function of the first kind, and,
Figure 1 Notation for semiinfinite plate scattering. 
For convenience, we note that the form of (1) is that of calculating the sound from a source and its image in the plane y = 0. If we take θ_{1} as the coordinate of the source and define θ_{2} = θ_{1} − 2π as the coordinate of the image, the acoustic field can be calculated as the sum of the fields g_{i} from the source and its image, using,(3)(4)
We rewrite (2) in a form which facilitates physical interpretation when applied to the rotor noise problem, and can be used to efficiently approximate the field in different regions. Using the result,we can write g_{i} in a number of alternative forms,(5)(6)where for convenience, we define the functions,(7)(8)
The evaluation of the Green’s function for scattering by the plate requires the evaluation of the integrals of (7) and (8). A solution for most of the far field will be found by approximating (8), while an exact expansion for (7) will be developed and used to find a solution for the remaining part of the field.
Integration by parts gives an asymptotic approximation for ,(9)so that for large ,(10)and H(·) is the Heaviside step function.
The asymptotic expression (10) is clearly unbounded for S_{i} → 0 and is invalid in the vicinity of S_{1,2} = 0. From the definition of S_{i}, it is clear that this is the region around the lines through the source and the trailing edge and through the image source and the edge, Figure 2.
Figure 2 Contribution of acoustic source and image in different regions. Thick line: plate; solid lines: S_{1,2} = 0; dashed lines hyperbolae of (11). 
Jones [13] discusses the behaviour of the acoustic field in different regions in terms of geometric acoustics. Where S_{i} > 0, the freefield Green’s function is “switched on” and the field is that of a source and its reflection in the plane. Where S_{i} < 0, the plate blocks the direct contribution from the source and only the second term of (10) contributes, defining the “shadow” region. Near the boundaries of these two regions, the asymptotic expression breaks down. In the notation of this paper, the asymptotic expression is reasonable outside a region bounded by the hyperbola [13](11)with Jones taking A = 10 as a reasonable value. As well as the lines S_{i} = 0, Figure 2 shows the hyperbola of (11) for different values of A/K. The axis of the hyperbolae is S_{i} = 0 and they contract with increasing K. At low frequency the asymptotic approximation breaks down in a large region of the field. As K increases, geometric acoustics is a better approximation and more of the field is well modelled by the asymptotic formula.
In order to find an expansion which can be used for small S_{i}, we apply the product theorem for Bessel functions ([15], 8.530.2) to (6),(12)
Upon integration of the Bessel functions of the first kind,(13)which is exact for s < 1, though slow to converge as s → 1. This result can be used to evaluate the acoustic field in the region s → 0.
2.2 Acoustic field of a ring source near a trailing edge
We now apply the results of Section 2.1 to the estimation of the acoustic field of a rotating source impinging on the edge of a semiinfinite plate. The system is modelled as a ring source and its image in the plane, with the field of each calculated using the “partial” Green’s function G_{1,2} with,(14)with the principal source denoted by subscript 1 and its image by subscript 2.
As is standard for rotor noise problems [16–20], the source is taken to vary as exp[inψ_{0}] where ψ_{0} is the angular variable on a circular source. To respect the image system, the image ring source has azimuthal variation exp[−inψ_{0}] and its field can be calculated using the same analysis, changing n to −n.
The ring is centred at a point (x_{0}, h, 0) with coordinates on the source given by,where a is the radius of the source. We introduce spherical coordinates centred on each ring source (Fig. 3),
Figure 3 Coordinate system for evaluation of acoustic field of ring source. 
The acoustic field of each source is then given by,(15)
We now develop an approximation for p_{i} valid in the far field.
We treat the field as made up of two contributions, corresponding to the “direct” field generated by the ring source, and that scattered by the trailing edge. The “ring” term is the familiar integral,(16)for which a number of exact [20] and approximate [16, 18] expressions exist.
To evaluate the part of the field scattered by the trailing edge, we define the functions,(17)(18)
In the spherical coordinate system, is given by,
Differentiating with respect to a and neglecting terms less than O(1/R_{i}) yields a farfield approximation,which, upon insertion into (15) and use of tables ([15], 8.411), yields the familiar result for the acoustic field of a ring source ([16–18], among many others),where J_{n}(·) is the Bessel function of the first kind. The freefield part of the ringsource field is then given by,(19)
We can apply a similar approach to the approximation of the scattered field. Given,to first order in a,
Using Neumann’s addition theorem ([21], 10.23),
With the use of tables ([15], 6.681.8, ~9), it is readily shown that for n and q both odd or both even, the integral,(20)and is identically zero otherwise. This yields,where n = 2n′ + δ, δ = 0, 1.
The part of the ringsource field scattered by the trailing edge,is then approximated by,(21)
This approximation breaks down between the freefield being switched on or off where S_{i} is small (v_{0} ≈ R_{i}) and a different approximation is required in this region.
Again, we proceed by approximating for the far field and using the properties of Bessel functions to find a form suitable for evaluation.
Returning to (13),and noting that , we seek an approximation which can be inserted into (15) and integrated. In the far field, , the difficulty lies in capturing the rapid variation in as s_{i} → 0. We proceed as follows to develop a tractable farfield approximation. The Hankel function is replaced by an approximation valid to first order in a, using the standard relations for derivatives,
The argument of the Bessel function of the first kind is approximated by,and again using the product theorem ([15], 8.530.2),yielding,(22)where all source coordinates such as are evaluated at a = 0, the centre of the ring. Using (20), for n = 2n′,(23)where the auxiliary quantities are,
2.3 Summary
To summarize, the farfield sound from a rotor near the edge of a semiinfinite plane can be estimated by summing the contribution from the circular source of azimuthal order n and from its image in the plane, of order −n. For each source, the acoustic field is estimated by first determining the appropriate farfield approximation to apply. Figure 4 shows the region around a rotor divided according to the sign of S_{i}, with the hyperbolae of (11) added for source positions at the top and bottom of the rotor, with A = 10 and , which corresponds to the sample calculations presented in Section 3. In region I, S_{i} > 0 for all source positions on the rotor while in region II, S_{i} < 0. In region III, S_{i} changes sign for some value of ψ_{0}. The appropriate farfield approximation to use in each region is then:(24)(25)(26)
Figure 4 Regions around rotor labelled by farfield approximation. The hyperbolae of (11) are shown for the top and bottom of the rotor with A = 10 and . 
In the far field, the functions , , and can be evaluated using the results given earlier. Finally, with regard to evaluation of the series defining these functions, we note that the Bessel function of the first kind J_{n}(x) decays exponentially with increasing order for n > x, allowing the series to be truncated with negligible loss of accuracy.
3 Results
To illustrate the application of the method, we present sample results for an arbitrarily selected configuration, with rotor parameters a = 0.3, n = 6. The rotor is positioned above the plate at h = 0.9, and one rotor diameter upstream of the trailing edge at x_{0} = −2a. The rotor tip Mach number M_{t} is set to 0.6, so that the wavenumber k = nM_{t}/a = 12, and the flow Mach number M_{0} = 0.15. The acoustic field is evaluated using the methods of this paper, and compared to full numerical evaluation, with results calculated above and below the plate to examine the shielding effect.
Figure 5 shows the real and imaginary part of the potential at −16a ≤ x − x_{0} ≤ 16a, z = 0, i.e. directly above and below the source centre. Results are calculated at a constant vertical displacement above and below the source, y = h ± 16a. The two upper plots show the acoustic potential above the source and the plate, and the lower plots show the field below the plate, at the same distance from the source as in the upper plots. The region marked “III” on each plot shows where (26) has been applied, in the transition region where the asymptotic approximation for the edgescattered field breaks down. The beginning of this breakdown is apparent at the end of region III, in particular in the lower lefthand plot of the figure, where the difference between the asymptotic approximation and the numerical evaluation is clear for (x − x_{0})/a ⪆ 0. This corresponds to the hyperbolic boundary shown in Figure 4, which has been drawn for the same value of K as used in the calculations.
Figure 5 Acoustic potential above and below source; lefthand column: real part; righthand column: imaginary part; solid line: numerical; dashed line: approximation. Top row: field above source and plate; bottom row: field below source and plate. 
In applications, where the rotor may be placed above a wing in order to benefit from shielding effects, the region of interest is the “shadow zone” upstream of the trailing edge. The upper and lower fields are computed at constant distance from the source, so the different scales on the upper and lower plots make the shielding effect clear. In this case, the maximum amplitude upstream of the trailing edge is about ten times greater above the plate than below, and is well predicted by the far field approximation.
We note that while the results presented demonstrate good accuracy, the analysis is limited by the assumptions made in its development. In particular, the analysis does assume small source radius a and numerical experimentation has found that the accuracy of predictions degrades as a is increased. This may limit the applicability of the method, in particular as a becomes comparable to h, the case of a rotor with a small tip clearance above the wing, or where the rotor lies close to the trailing edge.
4 Conclusions
An approximate analysis has been developed for the radiation of sound from a rotating source near the edge of a semiinfinite plate in a uniform flow, a model problem for shielding and scattering of rotor noise by a wing. Sample calculations for small source radius show good agreement with full numerical evaluation, and capture the wing shielding effect reasonably accurately. Future work will focus on improving the accuracy and range of validity of the approximation, in particular in the case of small clearance between the rotor and wing. An open question is that of whether there is a useful exact expansion for the acoustic field, comparable to the series solutions which exist for isolated rotors.
Conflict of interest
The author declares that he has no conflicts of interest in relation to this article.
Acknowledgments
The author is indebted to the anonymous reviewer who brought the paper of Jones [13] to his attention.
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Cite this article as: Carley M. 2022. Shielding of rotor noise by plates and wings. Acta Acustica, 6, 27.
All Figures
Figure 1 Notation for semiinfinite plate scattering. 

In the text 
Figure 2 Contribution of acoustic source and image in different regions. Thick line: plate; solid lines: S_{1,2} = 0; dashed lines hyperbolae of (11). 

In the text 
Figure 3 Coordinate system for evaluation of acoustic field of ring source. 

In the text 
Figure 4 Regions around rotor labelled by farfield approximation. The hyperbolae of (11) are shown for the top and bottom of the rotor with A = 10 and . 

In the text 
Figure 5 Acoustic potential above and below source; lefthand column: real part; righthand column: imaginary part; solid line: numerical; dashed line: approximation. Top row: field above source and plate; bottom row: field below source and plate. 

In the text 
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