Sonic boom propagation revisited: A nonlinear geometrical acoustic model

Berci, Marco; Vigevano, Luigi

doi:10.1016/j.ast.2011.08.003

Cited by 3 publications

(2 citation statements)

References 48 publications

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“…which can propagate weak shock waves of isentropic behaviour in the low-supersonic regime [72], since the related entropy variations are of higher order, and first-principle integral constraints such as the "equal area rule" grant a physically consistent solution by fitting the necessary flow discontinuities [13,59]. The pressure coefficient C p (s w , t) then reads [23,24]:…”

Section: Governing Physics: From Nonlinear Compressible To Linear Incompressible Flowmentioning

confidence: 99%

On the Incipient Indicial Lift of Thin Wings in Subsonic Flow: Acoustic Wave Theory with Unsteady Three-Dimensional Effects

Berci¹

2022

Acoustics

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Enhanced approximate expressions for the incipient indicial lift of thin wings in subsonic potential flow are presented in this study, featuring explicit analytical corrections for the unsteady downwash. Lifting-line and acoustic-wave theories form the basis of the method, within an effective synthesis of the governing physics, which grants a consistent generalised framework and unifies previous works. The unsteady flow perturbation consists of a step-change in angle of attack or a vertical sharp-edged gust. The proposed model is successfully evaluated against numerical results in the literature for the initial airload development of elliptical and rectangular wings with a symmetric aerofoil, considering several aspect ratios and Mach numbers. While nonlinear downwash and compressibility terms demonstrate marginal (especially for the case of a travelling gust), both linear and nonlinear geometrical effects from a significant taper ratio, sweep angle or curved leading-edge are found to be more important than linear downwash corrections (which are crucial for the circulation growth at later times instead, along with linear compressibility corrections). The present formulae may then be used as a rigorous reduced-order model for validating higher-fidelity tools and complex simulations in industrial practice, as well as for estimating parametric sensitivities of unsteady aerodynamic loads within the preliminary design of aircraft wings in the subsonic regime.

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Section: Governing Physics: From Nonlinear Compressible To Linear Incompressible Flowmentioning

confidence: 99%

On the Incipient Indicial Lift of Thin Wings in Subsonic Flow: Acoustic Wave Theory with Unsteady Three-Dimensional Effects

Berci¹

2022

Acoustics

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“…There are now two methods for boom propagation: the Carlson simplified sonic boom prediction method [47] and the Thomas waveform parameter method [48]. The Thomas waveform parameter method is based on geometrical acoustics [49]. Figure 11 shows a brief schematic of the sonic boom propagation with the waveform parameter method.…”

Section: Sonic Boom Predictionmentioning

confidence: 99%

Low-boom low-drag optimization in a multidisciplinary design analysis optimization environment

Sun

Smith

2019

Aerospace Science and Technology

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This paper introduces a multidisciplinary design analysis and optimization environment called GENUS. The GENUS aircraft design environment's key features are that it is modular, expandable, flexible, independent, and sustainable. This paper discusses the application of this environment to the design of supersonic business jets (SSBJs). SSBJs are regarded as the pioneers of the next generation of supersonic airliners. Methodologies appropriate to SSBJs are developed in the GENUS environment. The Mach plane cross-sectional area is calculated based on the parametric geometry model. PANAIR is integrated to perform automated aerodynamic analysis. The drag coefficient is corrected by the Harris wave drag calculation and form factor method. The sonic boom intensity is predicted by the wave form parameter method, which is validated by PCBoom. The Cranfield E-5 SSBJ is chosen as a baseline configuration. Low-boom and low-drag optimization are carried out based on this configuration. Through the optimization, the sonic boom intensity is mitigated by 71.36% and the drag decreases by 20.65%.

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Flow simulation of a supersonic airplane with installed engine nacelle

Kim

Lee

2021

Aerospace Science and Technology

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Sonic boom propagation revisited: A nonlinear geometrical acoustic model

Cited by 3 publications

References 48 publications

On the Incipient Indicial Lift of Thin Wings in Subsonic Flow: Acoustic Wave Theory with Unsteady Three-Dimensional Effects

On the Incipient Indicial Lift of Thin Wings in Subsonic Flow: Acoustic Wave Theory with Unsteady Three-Dimensional Effects

Low-boom low-drag optimization in a multidisciplinary design analysis optimization environment

Flow simulation of a supersonic airplane with installed engine nacelle

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