A Study of Busemann-Type Biplane for Avoiding Choked Flow

Yamashita, Hiroshi; Yonezawa, Masahito; Obayashi, Shigeru; Kusunose, Kazuhiro

doi:10.2514/6.2007-688

Cited by 19 publications

(18 citation statements)

References 2 publications

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“…Particularly, sonic boom must be reduced significantly to make supersonic transport (SST) feasible [2,3]. Kusunose et al [4][5][6][7][8] and Kuratani et al [9] have examined the biplane concept to design a low boom configuration. This concept allows significant reduction of sonic boom using a Busemann-type biplane.…”

Section: Doi: 102514/140215mentioning

confidence: 99%

Sonic Boom Variability Due to Homogeneous Atmospheric Turbulence

Yamashita

Obayashi

2009

Journal of Aircraft

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This study describes the nondeterministic effect of homogeneous atmospheric turbulence on sonic boom propagation. The Sears-Haack body was calculated in three dimensions by computational fluid dynamics in inviscid flow (Euler) mode to create the near-field pressure wave. The homogeneous atmospheric turbulence field was represented by the finite sum of discrete Fourier modes based on the von Karman and Pao energy spectrum. The sonic boom signature was then calculated by the modified waveform parameter method, considering a random velocity of homogeneous atmospheric turbulence. The results of this study indicated that atmospheric turbulence has a marked influence on sonic boom overpressure during its propagation to the ground. In comparison to the noturbulence condition, we found that the sonic boom decreased in 59% of the cases and increased in 41% of the cases. Thus, homogeneous atmospheric turbulence seems to favor a decrease, rather than an increase, in boom overpressure. In addition, we found that turbulence has a small effect on the propagation path from the flight altitude to the ground. Nonetheless, this small change in the propagation path may result in a variability, of the point at which the sonic boom reaches the ground, of up to 1820 ft in the north-south direction (flight direction) and 115 ft in the east-west direction.

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Section: Doi: 102514/140215mentioning

confidence: 99%

Sonic Boom Variability Due to Homogeneous Atmospheric Turbulence

Yamashita

Obayashi

2009

Journal of Aircraft

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“…Group of researchers at various Japanese institutions have published a series of papers discussing various aspects of Busemann biplane through numerical simulations [9][10][11][12][13]. These researchers have studied the problems encountered by conventional supersonic biplane configurations at off design conditions and suggested design modifications through inverse design method.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigation of the effect of stagger on the aerodynamic characteristics of a Busemann biplane

Patidar

Yadav

Joshi

2016

Aerospace Science and Technology

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“…3,4) Briefly, this concept utilizes the shock wave interference and cancellation between the wings of the Busemann biplane; Adolf Busemann proposed that the sonic boom can be reduced using the interference between the shock wave and expansion fan. 3,4) CFD (Computational Fluid Dynamics) analyses [5][6][7][8] have been performed to verify this theory. Moreover, CFD analyses and the inverse design method [9][10][11][12] have been applied to supersonic biplane conceptual design and have been shown to produce effective results.…”

Section: Introductionmentioning

confidence: 99%

Experimental and Computational Studies of Low-Speed Aerodynamic Performance and Flow Characteristics around a Supersonic Biplane

Kuratani

Ozaki

Obayashi

et al. 2009

Trans. Japan Soc. Aero. S Sci.

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One of the most critical technical issues with regard to supersonic commercial transportation is the sonic boom that occurs during supersonic cruising flight, which causes impulsive noise on the ground. The ''supersonic biplane theory'' has been proposed to reduce the sonic boom. Shock wave interaction and cancellation between the wings of a supersonic biplane can be realized at a specific design Mach number, but does not work at off-design values. Here, the low-speed aerodynamic performance, as off-design performance, of a baseline supersonic biplane was investigated and discussed using experimental and computational fluid dynamics approaches. The thin airfoil stall characteristics of a supersonic biplane were shown to be caused by the stall of both upper and lower wings at an angle of attack of 20. Although there was leading flow separation of the upper wing at lower angles of attack, the stall of the lower wing was suppressed by interference with the upper wing. The lift of the lower wing was almost dominant to produce the lift of the supersonic biplane in the low-speed range. However, the lower wing caused greater drag than the upper wing at higher angles of attack.

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A Study of Busemann-Type Biplane for Avoiding Choked Flow

Cited by 19 publications

References 2 publications

Sonic Boom Variability Due to Homogeneous Atmospheric Turbulence

Sonic Boom Variability Due to Homogeneous Atmospheric Turbulence

Numerical investigation of the effect of stagger on the aerodynamic characteristics of a Busemann biplane

Experimental and Computational Studies of Low-Speed Aerodynamic Performance and Flow Characteristics around a Supersonic Biplane

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