December 4, 2025SAE International Journal of Aerospace

Impinging Shockwave/Boundary Layer Interaction–Induced Separation Mitigation Using Passive Control

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Passive control significantly mitigates shock-induced separation in a supersonic inlet model, improving flow stability.
The splitter plate reduces total pressure in the boundary layer while eliminating unsteady flows, enhancing operational efficiency.
Simulations were conducted using the Spalart–Allmaras turbulence model, validating results against experimental data for accuracy.
This approach may enable effective separation control in various applications, with implications for aerodynamics and propulsion systems.

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Implication

Computational analysis demonstrates that a splitter plate reduces flow unsteadiness and total pressure in a boundary layer, suggesting effective passive control for separation mitigation.

Cite This Study

Wahidi et al. (2025) studied this question.

synapsesocial.com/papers/6930e8bdea1aef094cca319e https://doi.org/10.4271/01-18-03-0014

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Implication

Computational analysis demonstrates that a splitter plate reduces flow unsteadiness and total pressure in a boundary layer, suggesting effective passive control for separation mitigation.

Impinging Shockwave/Boundary Layer Interaction–Induced Separation Mitigation Using Passive Control

Key Points

Discussion

Implication

Cite This Study

Impinging Shockwave/Boundary Layer Interaction–Induced Separation Mitigation Using Passive Control

Key Points

Discussion

Implication

Cite This Study

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