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Transactions on Aerospace Research
Édition 2024 (2024): Edition 1 (March 2024)
Accès libre
Various Blowing-Suction Schemes for Manipulating Turbulent Boundary Layers
Yevhenii Shkvar
Yevhenii Shkvar
,
E Shiju
E Shiju
,
Andrii Kryzhanovskyi
Andrii Kryzhanovskyi
et
Dmytro Redchyts
Dmytro Redchyts
| 13 mars 2024
Transactions on Aerospace Research
Édition 2024 (2024): Edition 1 (March 2024)
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Article Category:
research article
Publié en ligne:
13 mars 2024
Pages:
19 - 28
Reçu:
04 févr. 2022
Accepté:
08 janv. 2024
DOI:
https://doi.org/10.2478/tar-2024-0002
Mots clés
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).