Development of pressure-sensitive paint technique in a supersonic indraft wind tunnel and its application to a busemann biplane

K. Saito, H. Nagai, T. Ogawa, K. Asai

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

1 Citation (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 2-D theory. Referring to Schlieren picture 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 publication2007 22nd International Congress on Instrumentation in Aerospace Simulation Facilities, ICIASF
DOIs
Publication statusPublished - 2007 Dec 1
Event2007 22nd International Congress on Instrumentation in Aerospace Simulation Facilities, ICIASF - Pacific Grove, CA, United States
Duration: 2007 Jun 102007 Jun 14

Publication series

NameICIASF Record, International Congress on Instrumentation in Aerospace Simulation Facilities
ISSN (Print)0730-2010

Other

Other2007 22nd International Congress on Instrumentation in Aerospace Simulation Facilities, ICIASF
CountryUnited States
CityPacific Grove, CA
Period07/6/1007/6/14

ASJC Scopus subject areas

  • Instrumentation
  • Aerospace Engineering
  • Condensed Matter Physics

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