TY - GEN
T1 - Polymer/ceramic PSP with reduced surface roughness for unsteady pressure measurement in transonic flow
AU - Sugioka, Yosuke
AU - Numata, Daiju
AU - Asai, Keisuke
AU - Koike, Shunsuke
AU - Nakakita, Kazuyuki
AU - Nakajima, Tsutomu
N1 - Publisher Copyright:
© 2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All right reserved.
PY - 2016
Y1 - 2016
N2 - Polymer/ceramic pressure-sensitive paints (PC-PSPs) with reduced surface roughness were developed for measuring unsteady pressure fields in transonic flow. Four types of PC-PSPs, each having different particle size, mass content, solvent, and so on, were formulated and applied to transonic wind-tunnel tests of a Common Research Model airfoil. The effects of surface roughness on unsteady transonic flow on the airfoil were evaluated at Mach 0.85 and Reynolds number of 5.0 x 106. It was found that all four PC-PSPs had capabilities to measure time-series pressure distributions, but the location of a shock wave and the root-mean-square pressure fluctuations differed depending on types of PC-PSP. Among all tested PC-PSPs, the PC-PSP having arithmetic surface roughness of 0.5 μm and cutoff frequency of 3 kHz yielded data practically the same as that of a clean airfoil. Using this PC-PSP, propagation of pressure waves and oscillation of shock waves on the airfoil were clearly captured. A spectral analysis showed that the fundamental frequency of shock-wave oscillation agreed very well with that calculated based on the mechanism proposed by Lee. These results show that the selected PC-PSP can offer a powerful means to study transonic buffeting on airfoils and 3D wings.
AB - Polymer/ceramic pressure-sensitive paints (PC-PSPs) with reduced surface roughness were developed for measuring unsteady pressure fields in transonic flow. Four types of PC-PSPs, each having different particle size, mass content, solvent, and so on, were formulated and applied to transonic wind-tunnel tests of a Common Research Model airfoil. The effects of surface roughness on unsteady transonic flow on the airfoil were evaluated at Mach 0.85 and Reynolds number of 5.0 x 106. It was found that all four PC-PSPs had capabilities to measure time-series pressure distributions, but the location of a shock wave and the root-mean-square pressure fluctuations differed depending on types of PC-PSP. Among all tested PC-PSPs, the PC-PSP having arithmetic surface roughness of 0.5 μm and cutoff frequency of 3 kHz yielded data practically the same as that of a clean airfoil. Using this PC-PSP, propagation of pressure waves and oscillation of shock waves on the airfoil were clearly captured. A spectral analysis showed that the fundamental frequency of shock-wave oscillation agreed very well with that calculated based on the mechanism proposed by Lee. These results show that the selected PC-PSP can offer a powerful means to study transonic buffeting on airfoils and 3D wings.
UR - http://www.scopus.com/inward/record.url?scp=85007610190&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=85007610190&partnerID=8YFLogxK
U2 - 10.2514/6.2016-2018
DO - 10.2514/6.2016-2018
M3 - Conference contribution
AN - SCOPUS:85007610190
SN - 9781624103933
T3 - 54th AIAA Aerospace Sciences Meeting
BT - 54th AIAA Aerospace Sciences Meeting
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - 54th AIAA Aerospace Sciences Meeting, 2016
Y2 - 4 January 2016 through 8 January 2016
ER -