Pressure sensitive paint measurement in a hypersonic shock tunnel

Kazuyuki Nakakita, Takashi Yamazaki, Keisuke Asai, Norikazu Teduka, Atsuhiko Fuji, Masaharu Kameda

Research output: Contribution to conferencePaperpeer-review

27 Citations (Scopus)

Abstract

Pressure sensitive paint was applied to Mach 10 hypersonic flow. Short duration, 30ms, shock tunnel was used as a hypersonic wind tunnel. Because of its short flow duration, fast response binder-free anodized aluminum pressure sensitive paint was used in this study. Two types of 2-dimensional experimental model with anodized aluminum pressure sensitive paint; expansion comer model and compression comer model, were tested in a shock tunnel. Their surface pressure distributions for 4 angles of attack each were acquired. Reasonable images were measured respectively. The data of pressure sensitive paint was in good agreement with the data of reference pressure transducer and the standard deviation between the data of pressure sensitive paint and reference pressure transducer was 202 Pa. It was confirmed that pressure sensitive paint could be used enough for quantitative pressure distribution measurements in short duration hypersonic shock tunnel.

Original languageEnglish
DOIs
Publication statusPublished - 2000
Externally publishedYes
Event21st Aerodynamic Measurement Technology and Ground Testing Conference 2000 - Denver, CO, United States
Duration: 2000 Jun 192000 Jun 22

Conference

Conference21st Aerodynamic Measurement Technology and Ground Testing Conference 2000
CountryUnited States
CityDenver, CO
Period00/6/1900/6/22

ASJC Scopus subject areas

  • Engineering(all)

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