TY - GEN
T1 - First results of lifetime-based unsteady PSP measurement on a pitching airfoil in transonic flow
AU - Sugioka, Yosuke
AU - Nakakita, Kazuyuki
AU - Saitoh, Kenichi
AU - Nonomura, Taku
AU - Asai, Keisuke
N1 - Funding Information:
The authors wish to thank Tsutomu Nakajima, Koichi Suzuki, Hideki Yamaya, Hiroki Iwamoto, Aeronautical Technology Directorate, JAXA for their kind preparation of the wind-tunnel test. and all of the members of Supersonic Wind Tunnel Section We are also indebted to Norio Yoshimoto and all the members of Supersonic Wind Tunnel Section, Aeronautical Technology Directorate, JAXA, for their valuable support. The present study was supported by JSPS KAKENHI Grant Number 15H04050 and 16J02503.
Publisher Copyright:
© 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2018
Y1 - 2018
N2 - The objective of the present study is to measure pressure distributions on a forced pitching airfoil using a lifetime-based pressure-sensitive paint (PSP) technique. Before the wind tunnel testing, fluorescence response of polymer/ceramic PSP to pulse excitation was measured at various pressures and temperatures. Relative timing and lengths of two gates were selected so as to reduce and measurement error based on obtained fluorescence response is reduced. The wind tunnel test was conducted in the JAXA transonic flutter wind tunnel at Mach number of 0.74. NASA common research model airfoil was pitched sinusoidally at a frequency of 30 Hz. A non-uniform lifetime distribution under a uniform pressure and temperature condition was observed on the model. The effect of non-uniform lifetime distribution could be canceled by normalization using a lifetime image under the wind-off condition. As a result, phase-averaged pressure distributions on the airfoil were successfully measured. Moreover, the measurement error for lifetime-based method is almost half of that for intensity-based method in the present measurement conditions.
AB - The objective of the present study is to measure pressure distributions on a forced pitching airfoil using a lifetime-based pressure-sensitive paint (PSP) technique. Before the wind tunnel testing, fluorescence response of polymer/ceramic PSP to pulse excitation was measured at various pressures and temperatures. Relative timing and lengths of two gates were selected so as to reduce and measurement error based on obtained fluorescence response is reduced. The wind tunnel test was conducted in the JAXA transonic flutter wind tunnel at Mach number of 0.74. NASA common research model airfoil was pitched sinusoidally at a frequency of 30 Hz. A non-uniform lifetime distribution under a uniform pressure and temperature condition was observed on the model. The effect of non-uniform lifetime distribution could be canceled by normalization using a lifetime image under the wind-off condition. As a result, phase-averaged pressure distributions on the airfoil were successfully measured. Moreover, the measurement error for lifetime-based method is almost half of that for intensity-based method in the present measurement conditions.
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U2 - 10.2514/6.2018-1030
DO - 10.2514/6.2018-1030
M3 - Conference contribution
AN - SCOPUS:85044424278
SN - 9781624105241
T3 - AIAA Aerospace Sciences Meeting, 2018
BT - AIAA Aerospace Sciences Meeting
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Aerospace Sciences Meeting, 2018
Y2 - 8 January 2018 through 12 January 2018
ER -