Construction and Application of Transition Prediction Databased Method for 2<sup>nd</sup> Mode on Sharp Cone

Chanteux, Xavier; Bégou, Guillaume; Deniau, Hugues; Vermeersch, Olivier

doi:10.2514/6.2022-3470

Cited by 2 publications

(1 citation statement)

References 35 publications

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“…An isothermal boundary condition is prescribed for the linearised disturbances (T = 0 at wall). The code has been developed by Chanteux et al (2022) following the Saint-James (2020) framework and validated on a supersonic boundary layer by Nibourel et al (2023).…”

Section: Appendix D Wall-boundary Condition For Blowing and Heat Fluxmentioning

confidence: 99%

Adjoint-based linear sensitivity of a supersonic boundary layer to steady wall blowing–suction/heating–cooling

Poulain,

Content,

Rigas

et al. 2024

J. Fluid Mech.

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For a Mach $4.5$ flat-plate adiabatic boundary layer, we study the sensitivity of the first, second Mack modes and streaks to steady wall-normal blowing/suction and wall heat flux. The global instabilities are characterised in frequency space with resolvent gains and their gradients with respect to wall-boundary conditions are derived through a Lagrangian-based method. The implementation is performed in the open-source high-order finite-volume code BROADCAST and algorithmic differentiation is used to access the high-order state derivatives of the discretised governing equations. For the second Mack mode, the resolvent optimal gain decreases when suction is applied upstream of Fedorov's mode $S$ /mode $F$ synchronisation point, leading to stabilisation, and the converse when applied downstream. The largest suction gradient is in the region of branch I of mode $S$ neutral curve. For heat-flux control, strong heating at the leading edge stabilises both the first and second Mack modes, the former being more sensitive to wall-temperature control. Streaks are less sensitive to any boundary control in comparison with the Mack modes. Eventually, we show that an optimal actuator consisting of a single steady heating strip located close to the leading edge manages to damp the linear growth of all three instability mechanisms.

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Section: Appendix D Wall-boundary Condition For Blowing and Heat Fluxmentioning

confidence: 99%

Adjoint-based linear sensitivity of a supersonic boundary layer to steady wall blowing–suction/heating–cooling

Poulain,

Content,

Rigas

et al. 2024

J. Fluid Mech.

View full text Add to dashboard Cite

show abstract

Amplification factor transport equation modelling of Mack mode disturbances in hypersonic boundary layers

Xu,

Mu,

Wang

et al. 2024

Applied Mathematical Modelling

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Construction and Application of Transition Prediction Databased Method for 2^nd Mode on Sharp Cone

Cited by 2 publications

References 35 publications

Adjoint-based linear sensitivity of a supersonic boundary layer to steady wall blowing–suction/heating–cooling

Adjoint-based linear sensitivity of a supersonic boundary layer to steady wall blowing–suction/heating–cooling

Amplification factor transport equation modelling of Mack mode disturbances in hypersonic boundary layers

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Construction and Application of Transition Prediction Databased Method for 2nd Mode on Sharp Cone

Cited by 2 publications

References 35 publications

Adjoint-based linear sensitivity of a supersonic boundary layer to steady wall blowing–suction/heating–cooling

Adjoint-based linear sensitivity of a supersonic boundary layer to steady wall blowing–suction/heating–cooling

Amplification factor transport equation modelling of Mack mode disturbances in hypersonic boundary layers

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Construction and Application of Transition Prediction Databased Method for 2^nd Mode on Sharp Cone