Wing configuration effects on flow field and aerodynamic performance of supersonic biplane for sonic-boom reduction

Naoshi Kuratani, Masahito Yonezawa, Hiroshi Yamashita, Shuichi Ozaki, Toshihiro Ogawa, Shigeru Obayashi

Research output: Chapter in Book/Report/Conference proceedingConference contribution

2 Citations (Scopus)

Abstract

The "supersonic biplane theory" is one of the most effective concepts to reduce the sonic boom in supersonic flight. However, the unstart characteristics, that is choking phenomena, was one of the critical issues that disturb the shock wave cancellation between the wings of supersonic biplane. In this study, the shock wave behavior around the wing was visualized and discussed by Schlieren method. And the flow characteristics on the wing were investigated by pressure sensitive paints (PSP) and CFD analysis under the design and offdesign Mach number conditions. These surface pressure profiles on the wing of supersonic biplane clarified that the wave interaction between the oblique shock waves from the leading edge and Mach waves from the wing-tip was dominant of the start/unstart characteristics. Moreover, the two aspect ratio models were used to investigate the effect of aspect ratio on the shock wave interaction and cancellation. The lower aspect ratio achieved the shock wave cancellation, but the higher one did not achieve it under off-design Mach number conditions. The three dimensional flow outward, mainstream Mach number, boundary layer growth on the wing, model dimension and paint thickness were some influencing parameters of start characteristics.

Original languageEnglish
Title of host publicationICAS Secretariat - 26th Congress of International Council of the Aeronautical Sciences 2008, ICAS 2008
Pages3001-3010
Number of pages10
Publication statusPublished - 2008 Dec 1
Event26th Congress of International Council of the Aeronautical Sciences 2008, ICAS 2008 - Anchorage, AK, United States
Duration: 2008 Sep 142008 Sep 19

Publication series

NameICAS Secretariat - 26th Congress of International Council of the Aeronautical Sciences 2008, ICAS 2008
Volume2

Other

Other26th Congress of International Council of the Aeronautical Sciences 2008, ICAS 2008
CountryUnited States
CityAnchorage, AK
Period08/9/1408/9/19

Keywords

  • Aspect ratio
  • CFD
  • PSP
  • Shock wace cancellation
  • Supersonic biplane

ASJC Scopus subject areas

  • Aerospace Engineering
  • Control and Systems Engineering
  • Electrical and Electronic Engineering
  • Materials Science(all)

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  • Cite this

    Kuratani, N., Yonezawa, M., Yamashita, H., Ozaki, S., Ogawa, T., & Obayashi, S. (2008). Wing configuration effects on flow field and aerodynamic performance of supersonic biplane for sonic-boom reduction. In ICAS Secretariat - 26th Congress of International Council of the Aeronautical Sciences 2008, ICAS 2008 (pp. 3001-3010). (ICAS Secretariat - 26th Congress of International Council of the Aeronautical Sciences 2008, ICAS 2008; Vol. 2).