Skip to main content
SpringerLink
Log in

Control of self-induced roll oscillations using the sinusoidal leading-edge for low-aspect-ratio wings

  • Research Article
  • Published:
Experiments in Fluids Aims and scope Submit manuscript

Abstract

A study on attenuating the self-induced roll oscillations of low-aspect-ratio flat-plate wings was conducted experimentally in a wind tunnel facility using a bionic flow control approach of the sinusoidal leading-edge (SLE). It was found that the effectiveness of the SLE on roll attenuation strongly depends on its amplitude and wavelength. Velocity measurements indicated that the SLE can generate streamwise counter-rotating vortex pairs (CVPs). These CVPs induce downwash flow, resulting in a decline in height of the leading-edge separated flow, thus attenuating roll oscillations. Force measurement results suggest that by choosing the appropriate wavelength-to-amplitude ratio of the SLE, self-induced roll oscillations can be suppressed with improved lift characteristics of the wing.

Graphic abstract

This is a preview of subscription content, log in via an institution to check access.

Access this article

Log in via an institution

Price excludes VAT (USA)
Tax calculation will be finalised during checkout.

Instant access to the full article PDF.

Institutional subscriptions

Fig. 1
Fig. 2
Fig. 3
Fig. 4
Fig. 5
Fig. 6
Fig. 7
Fig. 8
Fig. 9
Fig. 10
Fig. 11
Fig. 12
Fig. 13
Fig. 14
Fig. 15
Fig. 16
Fig. 17
Fig. 18

Similar content being viewed by others

Abbreviations

A :

Amplitude of the sinusoidal leading-edge

AR:

Aspect ratio

b :

Wing span

c :

Root chord length of the baseline model

C l :

Roll moment coefficient

C L :

Lift coefficient, L/(½ρU2∞ S)

C L,α :

Lift curve slope

C D :

Drag coefficient, D/(½ρU2∞ S)

C M,c/4 :

Pitching moment coefficient, Mc/4/(½ρU2∞ Sc)

D :

Drag

f :

Frequency of roll oscillation

I xx :

Moment of inertia about the x-axis

L :

Lift

M c/4 :

Pitching moment about a quarter chord length

q ∞ :

Dynamic pressure of freestream, ½ρU2∞

Re:

Reynolds number, ρU∞c/μ

S :

Lifting surface area

St:

Strouhal number, fU∞/c

t :

Maximum thickness of the wing

u′ :

Velocity fluctuation in the streamwise direction

U :

Velocity magnitude

U ∞ :

Freestream velocity

v′:

Velocity fluctuation in the spanwise direction

x :

Streamwise coordinate

y :

Spanwise coordinate

z :

Normal to the freestream coordinate

α :

Wing angle of attack

β :

Sideslip angle

λ :

Wavelength of the sinusoidal leading-edge

λ/A :

Wavelength-to-amplitude ratio

Λ :

Sweep angle

μ :

Air viscosity

ρ :

Air density

Φ, \( \dot{\varPhi } \), \( \ddot{\varPhi } \) :

Roll angle, roll speed, roll acceleration

ω :

Vorticity

CVP:

Counter-rotating vortex pair

FFT:

Fast Fourier transform

LAR:

Low-aspect-ratio

LET:

Leading-edge tubercles

MAV:

Micro aerial vehicle

PIV:

Particle image velocimetry

TKE:

Turbulent kinetic energy, \( \frac{1}{2}(\overline{{u^{{{\prime }2}} }} + \overline{{v^{{{\prime }2}} }} ) \)

UAV:

Unmanned air vehicle

RMS, rms:

Root-mean-square

SLE:

Sinusoidal leading-edge

References

Download references

Acknowledgements

This work was supported by the Ministry-of-Education Key Laboratory of Fluid Mechanics (BUAA), Key Laboratory of Aero-Acoustics Ministry of Industry and Technology (BUAA), Hamburg University of Applied Sciences (HAW Hamburg) and the National Natural Science Foundation of China, under Grant Numbers 11850410440, 11772033 and 117221202.

Author information

Authors and Affiliations

  1. Key Laboratory of Aero-Acoustics Ministry of Industry and Information Technology (Lu Shijia Laboratory), Beihang University (BUAA), Beijing, 100191, China

    Tianxiang Hu, Peiqing Liu, Qiulin Qu & Hao Guo

  2. Shanghai Aircraft Design and Research Institute (SADRI), Commercial Aircraft Corporation of China (COMAC), Shanghai, 201210, China

    Changfu Cheng

  3. Key Laboratory of Fluid Mechanics Ministry of Education (Institute of Fluid Mechanics), Beihang University (BUAA), Beijing, 100191, China

    Tianxiang Hu, Yihuan Huang, Zhaosheng Zhang, Qiulin Qu & Hao Guo

  4. Department of Automotive and Aeronautical Engineering, Hamburg University of Applied Sciences (HAW Hamburg), Hamburg, Germany

    Rinie A. D. Akkermans

Authors
  1. Tianxiang Hu
    View author publications

    You can also search for this author in PubMed Google Scholar

  2. Changfu Cheng
    View author publications

    You can also search for this author in PubMed Google Scholar

  3. Peiqing Liu
    View author publications

    You can also search for this author in PubMed Google Scholar

  4. Yihuan Huang
    View author publications

    You can also search for this author in PubMed Google Scholar

  5. Zhaosheng Zhang
    View author publications

    You can also search for this author in PubMed Google Scholar

  6. Qiulin Qu
    View author publications

    You can also search for this author in PubMed Google Scholar

  7. Hao Guo
    View author publications

    You can also search for this author in PubMed Google Scholar

  8. Rinie A. D. Akkermans
    View author publications

    You can also search for this author in PubMed Google Scholar

Corresponding author

Correspondence to Peiqing Liu.

Additional information

Publisher's Note

Springer Nature remains neutral with regard to jurisdictional claims in published maps and institutional affiliations.

Rights and permissions

Reprints and permissions

About this article

Check for updates. Verify currency and authenticity via CrossMark

Cite this article

Hu, T., Cheng, C., Liu, P. et al. Control of self-induced roll oscillations using the sinusoidal leading-edge for low-aspect-ratio wings. Exp Fluids 61, 166 (2020). https://doi.org/10.1007/s00348-020-02988-6

Download citation

  • Received:

  • Revised:

  • Accepted:

  • Published:

  • DOI: https://doi.org/10.1007/s00348-020-02988-6

Search

Navigation