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Various Blowing-Suction Schemes for Manipulating Turbulent Boundary Layers Cover

Various Blowing-Suction Schemes for Manipulating Turbulent Boundary Layers

Transactions on Aerospace Research
Volume 2024 (2024): Issue 1 (March 2024)
By:
Open Access
|Mar 2024

Figures & Tables

Fig. 1.

The principal idea of the microblowing application to the aircraft streamlined surface.
The principal idea of the microblowing application to the aircraft streamlined surface.

Fig. 2.

Schematics of microblowing through the array of lateral slots (A) and longitudinally placed slots (B).
Schematics of microblowing through the array of lateral slots (A) and longitudinally placed slots (B).

Fig. 3.

Computational domain, mesh and its fragments.
Computational domain, mesh and its fragments.

Fig. 4.

Local skin friction coefficient Cf distribution along the longitudinal coordinate x of flow development around flat plate without (1) and with microblowing (2, 3): circles – Kornilov-Boiko experiments [6]; lines – Shkvar’s numerical predictions. Cases (A) and (B) correspond to the uniform and intermittent microblowing, respectively, with blowing intensity Cb = Vy/V∞ = 0.00277.
Local skin friction coefficient Cf distribution along the longitudinal coordinate x of flow development around flat plate without (1) and with microblowing (2, 3): circles – Kornilov-Boiko experiments [6]; lines – Shkvar’s numerical predictions. Cases (A) and (B) correspond to the uniform and intermittent microblowing, respectively, with blowing intensity Cb = Vy/V∞ = 0.00277.

Fig. 5.

The pressure coefficient distribution along the NACA0012 airfoil chord Cp(x/c). For α□= 4° (left) and α = 12° (right) in the reference configuration (mass transfer through the streamlined surface is absent).
The pressure coefficient distribution along the NACA0012 airfoil chord Cp(x/c). For α□= 4° (left) and α = 12° (right) in the reference configuration (mass transfer through the streamlined surface is absent).

Fig. 6.

The pressure coefficient distribution along the NACA0012 airfoil chord in the configuration α = 0° for suction influence through one of the airfoil sides with vn = −0.00687 U∞ (flux 263 l/min) – (A); and for the same suction influence, combined with blowing through the windward side with vn = 0.013 U∞ (flux 500 l/min) – (B).
The pressure coefficient distribution along the NACA0012 airfoil chord in the configuration α = 0° for suction influence through one of the airfoil sides with vn = −0.00687 U∞ (flux 263 l/min) – (A); and for the same suction influence, combined with blowing through the windward side with vn = 0.013 U∞ (flux 500 l/min) – (B).

Fig. 7.

TVelocity magnitude isolines in the boundary layer along wing span (z-coordinate).
TVelocity magnitude isolines in the boundary layer along wing span (z-coordinate).
DOI: https://doi.org/10.2478/tar-2024-0002 | Journal eISSN: 2545-2835
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Language: English
Page range: 19 - 28
Submitted on: Feb 4, 2022
Accepted on: Jan 8, 2024
Published on: Mar 13, 2024
Published by: Sciendo
In partnership with: Paradigm Publishing Services
Publication frequency: 4 times per year
Keywords:
combined flow control,
drag reduction,
blowing,
suction,
numerical flow modelling,
RANS,
experimental data analysis
Related subjects:
Engineering,
Introductions and overviews,
Engineering, other,
Geosciences,
Geosciences, other,
Materials sciences,
Materials sciences, other,
Physics,
Physics, other

© 2024 Yevhenii Shkvar, E Shiju, Andrii Kryzhanovskyi, Dmytro Redchyts, published by Sciendo
This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 License.

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