Computational modelling and analysis of porous bleed holes at supersonic speeds

Date

2020-01-01

Author

Akar, Gökhan
Eyi, Sinan

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© 2020, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.Shock Wave / Boundary Layer Interaction is an important issue that should be taken into account when studying inlet design. Bleed holes have traditionally been used to remove the lower momentum part of the boundary layer to avoid separation from adverse Shock Wave / Boundary Layer Interaction. In this study, modeling of porous bleed holes investigated in computational fluid dynamics on a flat plate with and without an oblique shock interaction. For the validation of the method, three-dimensional CFD simulations are performed on fully resolved models with modeling bleed plenum and hole cavity details. Due to the ease of modeling on complex geometries, it is aimed to evaluate the unstructured grid approach on bleed flow. A grid convergence study is conducted on different levels of grids using Spalart-Allmaras, Realizable k-ε and SST k-ω turbulence models. Optimal grid resolution and turbulence model are determined for bleed flow simulations. Further CFD analyzes are performed at different total pressure ratios (Ppl/Pt) and results are compared with experimental data. The comparisons show good agreement between numerical solutions and test data for both cases. The comparisons show that the numerical solutions are in good agreement with the test data for both cases.

URI

https://hdl.handle.net/11511/69586

DOI

https://doi.org/10.2514/6.2020-3721

Collections

Department of Aerospace Engineering, Conference / Seminar

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Citation Formats

G. Akar and S. Eyi, “Computational modelling and analysis of porous bleed holes at supersonic speeds,” 2020, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/69586.