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 language | English |
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| Publication status | Published - 2002 Jan 1 |
| Externally published | Yes |
| Event | 22nd AIAA Aerodynamic Measurement Technology and Ground Testing Conference 2002 - St. Louis, MO, United States Duration: 2002 Jun 24 → 2002 Jun 26 |
Other
| Other | 22nd AIAA Aerodynamic Measurement Technology and Ground Testing Conference 2002 |
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| Country/Territory | United States |
| City | St. Louis, MO |
| Period | 02/6/24 → 02/6/26 |
ASJC Scopus subject areas
- Aerospace Engineering