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.
|Publication status||Published - 2000|
|Event||21st Aerodynamic Measurement Technology and Ground Testing Conference 2000 - Denver, CO, United States|
Duration: 2000 Jun 19 → 2000 Jun 22
|Conference||21st Aerodynamic Measurement Technology and Ground Testing Conference 2000|
|Period||00/6/19 → 00/6/22|
ASJC Scopus subject areas