TY - JOUR
T1 - Experimental analysis of transonic buffet on a 3D swept wing using fast-response pressure-sensitive paint
AU - Sugioka, Yosuke
AU - Koike, Shunsuke
AU - Nakakita, Kazuyuki
AU - Numata, Daiju
AU - Nonomura, Taku
AU - Asai, Keisuke
N1 - Funding Information:
Acknowledgements The authors wish to thank the members of the Next Generation Aeronautical Innovation Hub Center and Wind Tunnel Technology Center, JAXA, for their kind preparation and operation of the wind-tunnel test. We gratefully acknowledge helpful discussions with Mr. Tsutomu Nakajima, Dr. Makoto Ueno, and Mr. Kodai Hiura. TiO2 samples used for the PSP binder were provided by Tayca Corporation. The present study was supported by JSPS KAKENHI Grant number JP16J02503.
Publisher Copyright:
© 2018, Springer-Verlag GmbH Germany, part of Springer Nature.
PY - 2018/6/1
Y1 - 2018/6/1
N2 - Transonic buffeting phenomena on a three-dimensional swept wing were experimentally analyzed using a fast-response pressure-sensitive paint (PSP). The experiment was conducted using an 80%-scaled NASA Common Research Model in the Japan Aerospace Exploration Agency (JAXA) 2 m × 2 m Transonic Wind Tunnel at a Mach number of 0.85 and a chord Reynolds number of 1.54 × 106. The angle of attack was varied between 2.82° and 6.52°. The calculation of root-mean-square (RMS) pressure fluctuations and spectral analysis were performed on measured unsteady PSP images to analyze the phenomena under off-design buffet conditions. We found that two types of shock behavior exist. The first is a shock oscillation characterized by the presence of “buffet cells” formed at a bump Strouhal number St of 0.3–0.5, which is observed under all off-design conditions. This phenomenon arises at the mid-span wing and is propagated spanwise from inboard to outboard. The other is a large spatial amplitude shock oscillation characterized by low-frequency broadband components at St < 0.1, which appears at higher angles of attack (α ≥ 6.0°) and behaves more like two-dimensional buffet. The transition between these two shock behaviors correlates well with the rapid increase of the wing-root strain fluctuation RMS.
AB - Transonic buffeting phenomena on a three-dimensional swept wing were experimentally analyzed using a fast-response pressure-sensitive paint (PSP). The experiment was conducted using an 80%-scaled NASA Common Research Model in the Japan Aerospace Exploration Agency (JAXA) 2 m × 2 m Transonic Wind Tunnel at a Mach number of 0.85 and a chord Reynolds number of 1.54 × 106. The angle of attack was varied between 2.82° and 6.52°. The calculation of root-mean-square (RMS) pressure fluctuations and spectral analysis were performed on measured unsteady PSP images to analyze the phenomena under off-design buffet conditions. We found that two types of shock behavior exist. The first is a shock oscillation characterized by the presence of “buffet cells” formed at a bump Strouhal number St of 0.3–0.5, which is observed under all off-design conditions. This phenomenon arises at the mid-span wing and is propagated spanwise from inboard to outboard. The other is a large spatial amplitude shock oscillation characterized by low-frequency broadband components at St < 0.1, which appears at higher angles of attack (α ≥ 6.0°) and behaves more like two-dimensional buffet. The transition between these two shock behaviors correlates well with the rapid increase of the wing-root strain fluctuation RMS.
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U2 - 10.1007/s00348-018-2565-5
DO - 10.1007/s00348-018-2565-5
M3 - Article
AN - SCOPUS:85048133684
SN - 0723-4864
VL - 59
JO - Experiments in Fluids
JF - Experiments in Fluids
IS - 6
M1 - 108
ER -