Pressure-sensitive paint application to a wing-body model in a hypersonic shock tunnel

Kazuyuki Nakakita, Keisuke Asai

Research output: Contribution to conferencePaperpeer-review

18 Citations (Scopus)

Abstract

Pressure-sensitive paint (PSP) was applied to Mach 10 hypersonic wind tunnel tests. This experiment was conducted at a short-duration Shock Tunnel with the duration of 30ms. A fast response anodized aluminum pressure-sensitive paint (AA-PSP) was used as PSP. The response of AA-PSP is more than 10kHz. A chemical process to fabricate AA-PSP on models with complicated geometry was developed and applied to a 3-dimensional wing-body model. PSP measurement was conducted at two angles of attack, 0 degree and 20 degree, and images from various view angles and a close-up image were acquired for each case. A detailed pressure distribution pattern of complex flow phenomena including shock-wave/shock-wave interactions could be clearly measured with PSP. Effects of temperature rise during the test were also evaluated, and it was found that they were at negligible levels. PSP data was in good quantitative agreement with conventional pressure transducers even at the point where a strong interaction was observed.

Original languageEnglish
Publication statusPublished - 2002 Jan 1
Externally publishedYes
Event22nd AIAA Aerodynamic Measurement Technology and Ground Testing Conference 2002 - St. Louis, MO, United States
Duration: 2002 Jun 242002 Jun 26

Other

Other22nd AIAA Aerodynamic Measurement Technology and Ground Testing Conference 2002
CountryUnited States
CitySt. Louis, MO
Period02/6/2402/6/26

ASJC Scopus subject areas

  • Aerospace Engineering

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