TY - JOUR
T1 - Experimental comparison of shock buffet on unswept and 10-deg swept wings
AU - Sugioka, Yosuke
AU - Kouchi, Toshinori
AU - Koike, Shunsuke
N1 - Funding Information:
The present study was funded by the Japan Society for the Promotion of Science (Grant number 18H03814).
Funding Information:
The authors are grateful to Mr. Yo Matsumoto, Okayama University, for assistance with the experiments and analysis of the oil flow. The authors wish to thank Mr. Tsutomu Nakajima, Mr. Kazuyuki Nakakita, and the members of the Aerodynamics Research Unit, Aeronautical Technology Directorate, JAXA, for their kind preparation and operation of the wind tunnel test (TWT2-18-07, TWT2-20-01). We gratefully acknowledge support from Dr. Yuya Ohmichi, Aeronautical Technology Directorate, JAXA, for providing the code for the IPOD and DMD analysis and Dr. Atsushi Hashimoto and Dr. Sansica Andrea for discussion about the results. The present study was supported by JSPS KAKENHI Grant number 18H03814.
Publisher Copyright:
© 2022, The Author(s), under exclusive licence to Springer-Verlag GmbH Germany, part of Springer Nature.
PY - 2022/8
Y1 - 2022/8
N2 - Shock wave oscillations and surface flow fields on unswept-wing and 10 deg swept-wing models were experimentally investigated in a two-dimensional transonic wind tunnel facility to clarify the effects of wing sweep on the shock buffet phenomena. High-speed shadowgraph imaging, oil flow, and unsteady pressure-sensitive paint (PSP) techniques were used to visualize the shock oscillation over the models, surface stream lines, and the surface pressure distributions, respectively. Shock waves oscillated periodically on both models under specific flow conditions, but the oscillation frequency for the 10-deg swept wing was 1.4 times higher than that for the unswept wing. A spectral analysis and a mode decomposition analysis of PSP data for the 10 deg swept-wing model showed that higher-frequency shock oscillation developed mainly on the outboard wing, where a complicated 3D surface flow structure was formed. We confirmed that the wing sweep angle is an important factor affecting characteristic Strouhal number of shock buffet according to the present data and the results of previous studies. Graphical abstract: [Figure not available: see fulltext.].
AB - Shock wave oscillations and surface flow fields on unswept-wing and 10 deg swept-wing models were experimentally investigated in a two-dimensional transonic wind tunnel facility to clarify the effects of wing sweep on the shock buffet phenomena. High-speed shadowgraph imaging, oil flow, and unsteady pressure-sensitive paint (PSP) techniques were used to visualize the shock oscillation over the models, surface stream lines, and the surface pressure distributions, respectively. Shock waves oscillated periodically on both models under specific flow conditions, but the oscillation frequency for the 10-deg swept wing was 1.4 times higher than that for the unswept wing. A spectral analysis and a mode decomposition analysis of PSP data for the 10 deg swept-wing model showed that higher-frequency shock oscillation developed mainly on the outboard wing, where a complicated 3D surface flow structure was formed. We confirmed that the wing sweep angle is an important factor affecting characteristic Strouhal number of shock buffet according to the present data and the results of previous studies. Graphical abstract: [Figure not available: see fulltext.].
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U2 - 10.1007/s00348-022-03482-x
DO - 10.1007/s00348-022-03482-x
M3 - Article
AN - SCOPUS:85135942494
SN - 0723-4864
VL - 63
JO - Experiments in Fluids
JF - Experiments in Fluids
IS - 8
M1 - 132
ER -