Numerical Analysis of Busemann Biplane for Application to Boomless Supersonic Transport

Goto, Yuichiro; Kusunose, Kazuhiro; Yamashita, Hiroshi; Yonezawa, Masahito

doi:10.1299/jsmecmd.2004.17.117

Cited by 2 publications

(2 citation statements)

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“…However, at the design point, because of the entropy increase caused by the shock wave inside the biplane system (as shown in Fig. 4) and the nonlinear effect during the shock-expansion wave interaction processes [17,18], the zero wave drag condition of the Busemann airfoil design will not be actually realized. Kusunose [19] introduces Oswatitsch's wave drag expression, which can be used to predict this internal shock wave related wave drag.…”

Section: Wave Cancellation Effectmentioning

confidence: 99%

Adjoint-Based Aerodynamic Optimization of Supersonic Biplane Airfoils

Jameson

Wang

2012

Journal of Aircraft

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This paper addresses the aerodynamic performance of Busemann type supersonic bi-plane at off-design conditions. An adjoint based optimization technique is used to optimize the aerodynamic shape of the biplane to reduce the wave drag at a series of Mach numbers ranging from 1.1 to 1.7, at both acceleration and deceleration conditions. The optimized biplane airfoils dramatically reduces the effects of the choked flow and flow-hysteresis phenomena , while maintaining a certain degree of favorable shockwave interaction effects at the design Mach number. Compared to a diamond shaped single airfoil of the same total thickness, the wave drag of our optimized biplane is lower at almost all Mach numbers, and is significantly lower at the design Mach number.

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Section: Wave Cancellation Effectmentioning

confidence: 99%

Adjoint-Based Aerodynamic Optimization of Supersonic Biplane Airfoils

Jameson

Wang

2012

Journal of Aircraft

View full text Add to dashboard Cite

show abstract

“…4) and the nonlinear effect during the shock-expansion wave interaction processes [17,18], the zero wave drag condition of the Busemann airfoil design will not be actually realized. Kusunose [19] introduces Oswatitsch's wave drag expression, which can be used to predict this internal shock wave related wave drag.…”

Section: Wave Cancellation Effectmentioning

confidence: 99%

Adjoint based aerodynamic optimization of supersonic biplane airfoils

Jameson

Wang

2011

49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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This paper addresses the aerodynamic performance of Busemann-type supersonic biplanes at both design and offdesign conditions. An adjoint-based optimization technique is used to optimize the aerodynamic shape of the biplane to reduce the wave drag at a series of Mach numbers ranging from 1.1 to 1.7, at both acceleration and deceleration conditions. The optimized biplane airfoils dramatically reduces the effects of the choked flow and flow-hysteresis phenomena, while maintaining a certain degree of favorable shockwave interaction effects at the design Mach number. Compared with a diamond-shaped single airfoil of the same total thickness, the wave drag of our optimized biplane is lower at almost all Mach numbers, and is significantly lower at the design Mach number.

show abstract

Numerical Analysis of Busemann Biplane for Application to Boomless Supersonic Transport

Cited by 2 publications

References 0 publications

Adjoint-Based Aerodynamic Optimization of Supersonic Biplane Airfoils

Adjoint-Based Aerodynamic Optimization of Supersonic Biplane Airfoils

Adjoint based aerodynamic optimization of supersonic biplane airfoils

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