Experimental study on interference flow of a supersonic busemann biplane using pressure-sensitive paint technique

Hiroki Nagai, Soshi Oyama, Toshiyuki Ogawa, Naoshi Kuratani, Keisuke Asai

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

2 Citations (Scopus)

Abstract

Using Pressure Sensitive Paint, the pressure distributions on thin wings of the Busemann biplane model were measured in the small supersonic indraft wind tunnel. The observed phenomenon is so complicated that it is completely different from the prediction of the simple two-dimensional theory. Referring to Schlieren photograph and CFD analysis, it is found that these complex pressure fields are caused by the shock wave generated downstream just behind the wing ridge line. The results of this experiment show that the interference between Busemann biplane wings is sensitive to a small change in flow condition. A care must be taken in a wind tunnel test to realize the design condition of Busemann biplane where the shock waves are completely cancelled with each other.

Original languageEnglish
Title of host publicationICAS Secretariat - 26th Congress of International Council of the Aeronautical Sciences 2008, ICAS 2008
Pages3060-3068
Number of pages9
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

  • Busemann biplane
  • Pressure-Sensitive paint
  • Shock interference

ASJC Scopus subject areas

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

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  • Cite this

    Nagai, H., Oyama, S., Ogawa, T., Kuratani, N., & Asai, K. (2008). Experimental study on interference flow of a supersonic busemann biplane using pressure-sensitive paint technique. In ICAS Secretariat - 26th Congress of International Council of the Aeronautical Sciences 2008, ICAS 2008 (pp. 3060-3068). (ICAS Secretariat - 26th Congress of International Council of the Aeronautical Sciences 2008, ICAS 2008; Vol. 2).