A Study in the Supersonic Biplane Utilizing Its Shock Wave Cancellation Effect

Kusunose, Kazuhiro; Matsushima, Kisa; Goto, Yuichiro; Maruyama, Daïgo; Yamashita, Hiroshi; Yonezawa, Masahito

doi:10.2322/jjsass.55.1

Cited by 12 publications

(6 citation statements)

References 5 publications

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“…Then they designed a 2-D supersonic biplane that has the desired aerodynamic performance with an inverse design technique. [3][4][5] The designed 2-D biplane demonstrated a remarkable drag reduction during supersonic flow. Since then, supersonic biplane concepts have mostly been investigated by 2-D numerical flow simulation, and valuable aerodynamic results have been obtained.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Characteristics of Busemann Biplane by Wake Measurements in Low-Speed Wind Tunnel

Kashitani

Duong

Kusunose

et al. 2021

Trans. Japan Soc. Aero. S Sci.

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In this study, the basic aerodynamic characteristics of a Busemann biplane model in a low-speed wind tunnel were clarified by the wake survey technique. A low-speed wind tunnel of the blowdown type was used, and it had an exit nozzle size is in 1.5 m © 1.5 m. A wake measurement system and six-component balance system were installed in the test section. A five-hole probe was used in the wake measurement system to measure the velocity distribution. The Busemann biplane model was designed to cruise at Mach 1.7. The total length of the model was 742 mm, and the width was 556 mm. The shape of the fuselage was 76 mm square on a side, and the nose had a double-conical shape. The flow velocity was 20 m/s, and the Reynolds number derived from the mean chord length was 1.4 © 10 5 . The results of the study are summarized as follows. Based on the visualization of the wake flow, vortices were generated from the tips of the upper and lower wing elements of the biplane at an attack angle of ¡ = 0°, but the vortices had an opposing rotation direction. Analysis of the wake data showed that locally induced drag was not generated at the wing tip. At ¡ = 6°and 8°, the profile drag increased, probably due to the influence of the flow separation from the upper surface of the upper wing element. However, the total lift coefficient increased with an increasing angle of attack, even at ¡ > 8°. Therefore, it can be concluded that the biplane lift is mainly generated by the lower wing elements.

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Section: Introductionmentioning

confidence: 99%

Aerodynamic Characteristics of Busemann Biplane by Wake Measurements in Low-Speed Wind Tunnel

Kashitani

Duong

Kusunose

et al. 2021

Trans. Japan Soc. Aero. S Sci.

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“…The three-dimensional rectangular biplane showed that two-dimensional compression/expansion wave interaction was disturbed at the wing tip due to the spilling flow, which caused an increase in drag at an angle of attack of zero. 11,12) Therefore, the tip plates were expected to suppress spilling flow from the wing tip and to help maintain the two-dimensional wave interaction at the design point. As a result, the sonic boom and wave drag were expected to be reduced.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Characteristics and Effects of Winglets of the Boomless Tapered Supersonic Biplane during the Starting Process

Yamashita¹,

Fujisono²,

Toyoda³

et al. 2013

AEROSPACE TECHNOLOGY JAPAN

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The aerodynamic characteristics and the effects of tip plates of a tapered supersonic biplane wing during the starting process were investigated by experimental and computational fluid dynamics (EFD/CFD). Three types of wing models were used: one with a tip plate covering only the aft-half of the wing tip (type-A); one with a tip plate covering the entire wing tip (type-B); and one without a tip plate (type-N). Experiments were conducted in a supersonic blowdown wind tunnel 600 × 600 mm in cross-section located at the high-speed wind tunnel facility of the Institute of Space and Astronautical Science (ISAS/JAXA). The flow conditions ranged from M ∞ = 1.5 to 1.9 in increments of 0.1. Pressure-sensitive paint was applied to measure the pressure distributions on the wing surface. CFD simulations were conducted for comparison with the experimental results and for detailed investigation of the effects of the Mach number. The tapered biplane wing without a tip plate is found to start between M ∞ = 1.8 and 1.9. The difference in starting Mach number between type-N and type-A is small. On the other hand, the starting Mach number of type-B is approximately 0.05 higher than that of type-N.

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“…In the same year, a project of SST that is extended from the classic Busemann biplane concept started at Tohoku University. It has been led by Kusunose and other researchers [9][10][11][12]. The goal of this project is to develop the idea of the supersonic biplane using modern technique, such as computational fluid dynamics (CFD) tools, advanced in the past 30 years, as well as to propose a practical biplane wing for low boom and low drag in supersonic flight.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic analysis and design of Busemann biplane: towards efficient supersonic flight

Maruyama

Kusunose

Matsushima

et al. 2011

Proceedings of the Institution of Mechanical Engineers, Part G:

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Aiming to realize a low-drag supersonic transport, Busemann biplane concept was adopted in this study. Two-and three-dimensional (2D and 3D) biplanes were analysed and designed to improve their aerodynamic performance using computational fluid dynamics. It was confirmed that 3D biplane wings have better aerodynamic-performance areas than 2D biplane airfoils. A winglet is also useful for improvement of their aerodynamic performance. Aerodynamic characteristics of these biplanes at their off-design conditions were also analysed. In 3D wings, a flow choking and its attendant hysteresis as starting problems, which arise when the biplanes accelerate from low Mach numbers, disappear at lower Mach numbers than those in 2D airfoils. It was confirmed that hinged slats and flaps are effective to settle these issues. Finally, interference effects of a body with the biplanes were investigated. When the biplane wings are affected by the expansion waves from the body, their aerodynamic performance at the design Mach number and the starting Mach number are better and lower than those of their isolated wings, respectively. A 3D biplane wing obtained by an inverse-design method was applied to the body. The wing of this wing-body configuration achieves higher aerodynamic performance than the 2D flat-plate airfoil at sufficient lift conditions, which is the almost identical performance of 2D biplane airfoils.

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A Study in the Supersonic Biplane Utilizing Its Shock Wave Cancellation Effect

Cited by 12 publications

References 5 publications

Aerodynamic Characteristics of Busemann Biplane by Wake Measurements in Low-Speed Wind Tunnel

Aerodynamic Characteristics of Busemann Biplane by Wake Measurements in Low-Speed Wind Tunnel

Aerodynamic Characteristics and Effects of Winglets of the Boomless Tapered Supersonic Biplane during the Starting Process

Aerodynamic analysis and design of Busemann biplane: towards efficient supersonic flight

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