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Transactions on Aerospace Research
Volume 2024 (2024): Issue 1 (March 2024)
Open Access
Various Blowing-Suction Schemes for Manipulating Turbulent Boundary Layers
Yevhenii Shkvar
Yevhenii Shkvar
,
E Shiju
E Shiju
,
Andrii Kryzhanovskyi
Andrii Kryzhanovskyi
and
Dmytro Redchyts
Dmytro Redchyts
| Mar 13, 2024
Transactions on Aerospace Research
Volume 2024 (2024): Issue 1 (March 2024)
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Article Category:
research article
Published Online:
Mar 13, 2024
Page range:
19 - 28
Received:
Feb 04, 2022
Accepted:
Jan 08, 2024
DOI:
https://doi.org/10.2478/tar-2024-0002
Keywords
combined flow control
,
drag reduction
,
blowing
,
suction
,
numerical flow modelling
,
RANS
,
experimental data analysis
© 2024 Yevhenii Shkvar et al., published by Sciendo
This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.
Fig. 1.
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).
Fig. 3.
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.
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).
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).
Fig. 7.
TVelocity magnitude isolines in the boundary layer along wing span (z-coordinate).