Noise field of a propeller with angular inflow

Stuff, R.

doi:10.2514/3.9969

Cited by 14 publications

(12 citation statements)

References 13 publications

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“…Methods include both time-domain (Farassat, 1975) and frequency domain (Dahan, Avezard, Guillien, Malarmey & Chombart, 1981;Gounet & Lewy, 1988) techniques. There are several variations in the propeller problem, including single propeller noise (Hanson, 1980a(Hanson, , b, 1983Farassat & Succi, 1980;Farassat, 1981;Schulten, 1988;En via, 1994), counter-rotating propellers (Hubbard, 1948;Hanson, 1985;Tam, Salikuddin & Hanson, 1988;Parry & Crighton, 1986) and effects of mean flow (Tam & Sallikudin, 1986;Jou, 1989;Stuff, 1988;Mani, 1990;Krejsa, 1990;Envia, 1991;Canard & Carvana, 1994). The present paper addresses one aspect of the latter problem, viz.…”

Section: Introductionmentioning

confidence: 98%

On the Influence of Angle-of-Attack or Sideslip on Far-Field Propeller Noise

Campos¹

1999

Journal of Vibration and Acoustics

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The effect of angle-of-attack or sideslip on noise radiation by a propeller is considered, (Fig. 3). For a single propeller, neglecting installation effects, the angles of attack and sideslip can be combined (Fig. 2). The simplest model of the propeller, as a point multipole source, leads to an effect of inflow angle on acoustic radiation intensity, which is specified by the Doppler factor (Fig. 1). This simple model gives results consistent with experiments (Zandbergen, Sarin & Donnely, 1984, 1990, with a scaled propeller in a wind tunnel; the simple alberaic formula (Section 2), gives better results than a more elaborate numerical method (Sued, 1979). Proceeding to consider finite source distributions along the blades, leads to a less simple analytical theory (Section 3), based on radiation integrals valid in the far-field. It allows the consideration of unsteady monopole, dipole and quadrupole sources. This analytical theory, allowing for a distribution of acoustic sources along the span of the blades, gives a non-negligible correction to the algebraic theory. Thus the latter is adequate only as a simple order-of-magnitude estimate of noise level; a more acurate calculation noise levels requires evaluation of the radiation integrals, based on a knowledge of the acoustic source distribution.

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Section: Introductionmentioning

confidence: 98%

On the Influence of Angle-of-Attack or Sideslip on Far-Field Propeller Noise

Campos¹

1999

Journal of Vibration and Acoustics

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“…This purely acoustic e!ect was initially studied by Stu! [19] and later by Mani [20], Hanson and Parzych [21], Envia [22] and Hanson [23]. With the exception of reference [21], these studies were analytical and aimed at understanding the physics of the acoustic process as well as providing prediction methods.…”

Section: Wobbling Modesmentioning

confidence: 99%

“…[19] used near"eld and far"eld point-force approximations to estimate the e!ect of cross#ow on the acoustic "eld of a rotating source. It can thus be considered an extension of the earlier work of Gutin [9] or of Lowson [24].…”

Section: Wobbling Modesmentioning

confidence: 99%

The Structure of Wobbling Sound Fields

Carley

2001

Journal of Sound and Vibration

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“…The first theory of aerodynamic noise applies equally [18][19][20][21][22][23] well to the to thickness (monopole), loading (dipole) and turbulence (quadrupole) noise of aircraft propellers [24][25][26][27][28][29][30][31][32][33][34][35][36][37][38][39][40] (Section 2.1.1), helicopter rotors [41][42][43][44][45][46][47][48][49][50][51][52][53][54][55] (Section 2.1.2) and turbomachinery [56][57][58][59][60][61] requiring that the aerodynamic problem be solved first to specify the sources. The blade-vortex interaction noise (BVI) involves sound radiation by noise sources convected in a non-uniform flow, that does not match so well the assumptions of the first theory of aerodynamic sound of an unbounded medium at rest or in uniform motion with static or moving sources.…”

Section: Helicopter Rotor Noisementioning

confidence: 99%

On Physical Aeroacoustics with Some Implications for Low-Noise Aircraft Design and Airport Operations

Campos

2015

Aerospace

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Air traffic is growing at a steady rate of 3% to 5% per year in most regions of the world, implying a doubling every 15-25 years. This requires major advances in aircraft noise reduction at airports, just not to increase the noise exposure due to the larger number of aircraft movements. In fact it can be expected, as a consequence of increased opposition to noise by near airport residents, that the overall noise exposure will have to be reduced, by bans, curfews, fines, and other means and limitations, unless significantly quieter aircraft operations are achieved. The ultimate solution is aircraft operations inaudible outside the airport perimeter, or noise levels below road traffic and other existing local noise sources. These substantial noise reductions cannot come at the expense of a degradation of cruise efficiency, that would affect not just economics and travel time, but would increase fuel consumption and emission of pollutants on a global scale. The paper reviews the: (i) current knowledge of the aircraft noise sources; (ii) the sound propagation in the atmosphere and ground effects that determine the noise annoyance of near-airport residents; (iii) the noise mitigation measures that can be applied to current and future aircraft; (iv) the prospects of evolutionary and novel aircraft designs towards quieter aircraft in the near term and eventually to operations inaudible outside the airport perimeter. The 20 figures and 1 diagram with their legends provide a visual summary of the review.

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Noise field of a propeller with angular inflow

Cited by 14 publications

References 13 publications

On the Influence of Angle-of-Attack or Sideslip on Far-Field Propeller Noise

On the Influence of Angle-of-Attack or Sideslip on Far-Field Propeller Noise

The Structure of Wobbling Sound Fields

On Physical Aeroacoustics with Some Implications for Low-Noise Aircraft Design and Airport Operations

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