An effect of small angle of attack on disturbances evolution in swept wing boundary layer at Mach number M=2
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http://aip.scitation.org/doi/pdf/10.1063/1.5065250
Reference11 articles.
1. Basic experiments on transition in three-dimensional boundary layers dominated by crossflow instability
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4. The influence of flow parameters on the transition to turbulence in supersonic boundary layer on swept wing
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1. Effect of Small Angles of Attack on Turbulence Generation in Supersonic Boundary Layers on Swept Wings;Fluid Dynamics;2023-06
2. Effect of Small Angles of Attack on Turbulence Generation in Supersonic Boundary Layers on Swept Wings;Известия Российской академии наук. Механика жидкости и газа;2023-05-01
3. On a laminar-turbulent transition on swept wings with subsonic and supersonic leading adge;ACTUAL PROBLEMS OF CONTINUUM MECHANICS: EXPERIMENT, THEORY, AND APPLICATIONS;2023
4. Effect of Small Angles of Attack on Laminar-Turbulent Transition in the Supersonic Boundary Layer on a Swept Wing with χ = 72°;Fluid Dynamics;2022-02
5. An effect of unit Reynolds number on the laminar-turbulent transition on 3D swept wing with χ = 72° at M = 2;AIP Conference Proceedings;2021
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