Near-Field Sonic-Boom Prediction and Analysis with Hybrid Grid Navier–Stokes Solver

Ma, Boping; Wang, Gang; Ren, Jia; Ye, Zhengyin; Lei, Zhijin; Zha, Gecheng

doi:10.2514/1.c034659

Cited by 9 publications

(6 citation statements)

References 36 publications

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“…The partial enlarged details in Fig. 3 show that higher pressure magnitudes of shocks and expansions are obtained for the fine grids with less dissipation, which have shown in Refs [2,4].…”

Section: Mesh Convergencesupporting

confidence: 60%

“…H/L = 2. The real aircraft is assumed at an altitude of 16764 m and in a no-wind U.S. Standard Atmosphere [2].…”

Section: Resultsmentioning

confidence: 99%

“…Based on the modified supersonic linearization theory developed by Whitham [33], the linear far-field propagation methodology of Thomas [38] and geometrical acoustics, the authors' Division has developed an in-house package FL-BOOM [2] to estimate the effects of the far-field propagation. As a comprehensive sonic boom signal propagation and analysis tool, it has already been proved that FL-BOOM can provide an acceptable result for the prediction of sonic-boom signatures in Ref [2], and it is used to conduct the far-field calculation in this paper.…”

Section: Sonic-boom Predictionmentioning

confidence: 99%

“…Since the 21st century, a revived interest in civil supersonic flight has rekindled sonic boom research [1,2]. However, the mitigation of sonic booms, which can cause serious environmental problems for supersonic transport (SST), remains one of the biggest technical challenges for supersonic flight [3][4][5][6].…”

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

A low-boom and low-drag design method for supersonic aircraft and its applications on airfoils

et al. 2021

Adv. Aerodyn.

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Sonic boom reduction has been an urgent need for the development of future supersonic transport, because of the heavy damage of noise pollution. This paper provides a novel concept for supersonic aircraft to reduce the sonic boom and drag coefficient, wherein a suction slot near the leading edge and an injection slot near the trailing edge on the airfoil suction surface are opened. To make sure of a zero net mass flux flow control, the mass flow sucked in near the leading edge is equal to the mass flow injected near the trailing edge. The diamond and NACA0008 airfoils are adopted as the baseline airfoil to verify the capability of the proposed design method. The effects of the suction and injection location, the suction and injection slot size, the mass flow rate and the attack angle on the ground boom signature and drag coefficient are studied in detail. The results show that the optimized airfoils with the suction and injection have benefits in both sonic boom reduction and wave drag reduction. And the reduction of the sonic boom intensity is more sensitive to the injection near the trailing edge than the suction near the leading edge. From the viewpoint of aerodynamics, opening the suction and injection slots will have no adverse effect on the aerodynamic performances of the supersonic aircraft and even increase the lift-drag ratio under some circumstances. For energy saving, the suction and injection slots can be selectively opened, which are opened when the supersonic aircraft flies over the city but are closed when the aircraft flies over the sea.

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“…The partial enlarged details in Fig. 3 show that higher pressure magnitudes of shocks and expansions are obtained for the fine grids with less dissipation, which have shown in Refs [2,4].…”

Section: Mesh Convergencesupporting

confidence: 60%

“…H/L = 2. The real aircraft is assumed at an altitude of 16764 m and in a no-wind U.S. Standard Atmosphere [2].…”

Section: Resultsmentioning

confidence: 99%

Section: Sonic-boom Predictionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

A low-boom and low-drag design method for supersonic aircraft and its applications on airfoils

et al. 2021

Adv. Aerodyn.

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show abstract

“…Waveform Parameter method (32) is based on geometrical acoustics. This method is widely used in sonic boom prediction (23,(34)(35)(36)(37) . This method is suitable for programming to run automatically.…”

Section: Waveform Parameter Methodsmentioning

confidence: 99%

Low-boom low-drag solutions through the evaluation of different supersonic business jet concepts

Sun

Smith

2019

Aeronaut. j.

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This paper evaluates six supersonic business jet (SSBJ) concepts in a multidisciplinary design analysis optimisation (MDAO) environment in terms of their aerodynamics and sonic boom intensities. The aerodynamic analysis and sonic boom prediction are investigated by a number of conceptual-level numerical approaches. The panel method PANAIR is integrated to perform automated aerodynamic analysis. The drag coefficient is corrected by the Harris wave drag formula and form factor method. For sonic boom prediction, the near-field pressure is predicted through the Whitham F-function method. The F-function is decomposed to the F-function due to volume and the F-function due to lift to investigate the separate effect on sonic boom. The propagation method for the near-field signature in a stratified windy atmosphere is the waveform parameter method. In this research, using the methods described and publically available data on the concepts, the supersonic drag elements and sonic boom signature due to volume distribution and lift distribution are analysed. Based on the analysis, low-boom and low-drag design principles are identified.

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Resolution assessment of Reynolds stress model-based DES methods for high-lift device flow over 30P30N configuration

Wang,

Li,

Sun

2024

Aerospace Science and Technology

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Near-Field Sonic-Boom Prediction and Analysis with Hybrid Grid Navier–Stokes Solver

Cited by 9 publications

References 36 publications

A low-boom and low-drag design method for supersonic aircraft and its applications on airfoils

A low-boom and low-drag design method for supersonic aircraft and its applications on airfoils

Low-boom low-drag solutions through the evaluation of different supersonic business jet concepts

Resolution assessment of Reynolds stress model-based DES methods for high-lift device flow over 30P30N configuration

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