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Experimental analysis of transonic buffet on a 3D swept wing using fast-response pressure-sensitive paint

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Abstract

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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Change history

  • 03 June 2020

    There are typographical errors in the original publication of this article.

Abbreviations

C :

PSP calibration coefficient

C L :

Lift coefficient

C M :

Pitching moment coefficient

C P :

Pressure coefficient

C Prms :

RMS pressure fluctuations

\(C_{P}^{\prime }\) :

Dynamic component of pressure coefficient

Coh2 :

Coherence of the cross-spectrum

I :

PSP emission intensity

M ∞ :

Free-stream Mach number

M loc :

Local Mach number

N :

Number of data points

P :

Pressure

P 0 :

Total pressure

PSD:

Power spectral density

Re :

Reynolds number

S XX , S YY :

Auto-spectrum of X and Y

S XY :

Cross-spectrum between X and Y

St:

Strouhal number (= fcmac/U∞)

T :

Temperature

U ∞ :

Free-stream velocity

U C :

Convection velocity

b :

Span length

c :

Chord length

c mac :

Mean aerodynamic chord length

f :

Frequency

f S :

Frame rate of the camera

k + :

Roughness height

t :

Time

x :

Model chordwise location

y :

Model spanwise location

Δf :

Frequency resolution for FFT analysis

α :

Angle of attack

ϕ XY :

Phase shift of the cross-spectrum

η :

Spanwise location normalized by the half-span length

κ :

Reduced frequency (= 2πfc/U∞)

λ :

Spanwise wavelength

ave:

Time-averaged

ref:

Reference condition, 100 kPa

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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.

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Authors and Affiliations

  1. Department of Aerospace Engineering, Graduate School of Engineering, Tohoku University, 6-6-01 Aramaki-Aza-Aoba, Aoba-ku, Sendai, Miyagi, 980-8579, Japan

    Yosuke Sugioka, Daiju Numata, Taku Nonomura & Keisuke Asai

  2. Aeronautical Technology Directorate, Japan Aerospace Exploration Agency, Chofu, Tokyo, Japan

    Shunsuke Koike & Kazuyuki Nakakita

Authors
  1. Yosuke Sugioka
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  2. Shunsuke Koike
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  3. Kazuyuki Nakakita
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  4. Daiju Numata
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  5. Taku Nonomura
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  6. Keisuke Asai
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Corresponding author

Correspondence to Yosuke Sugioka.

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Sugioka, Y., Koike, S., Nakakita, K. et al. Experimental analysis of transonic buffet on a 3D swept wing using fast-response pressure-sensitive paint. Exp Fluids 59, 108 (2018). https://doi.org/10.1007/s00348-018-2565-5

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  • DOI: https://doi.org/10.1007/s00348-018-2565-5

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