Investigation on the adaptive control of shock wave/turbulent boundary layer interaction based on the secondary circulation jets

Zhong, Xiang-yu; Huang, Wei; Yan, Li; Wu, Han; Du, Zhao-bo

doi:10.1016/j.actaastro.2022.06.016

Cited by 18 publications

(2 citation statements)

References 52 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Based on the understanding of the nonlinear instability mechanisms, transition control has attracted considerable interest in the research community. Many methods can be used for controlling transition, such as wall blowing, 24,25 secondary recirculation jet, [26][27][28][29][30][31][32][33] and wall cooling and heating. 34 In addition, streaks have been applied successfully to control transition in both supersonic 35 and hypersonic flows.…”

Section: Introductionmentioning

confidence: 99%

Direct numerical simulation of mechanism and control of secondary instability induced transition in a supersonic boundary layer

Liu,

Huang,

Liu

2024

Physics of Fluids

View full text Add to dashboard Cite

Mechanisms and control of secondary-instability-induced-transition in a supersonic boundary layer are studied numerically via direct numerical simulation. The aim is to investigate and compare the transition mechanisms of fundamental, subharmonic, asymmetric subharmonic, and detuned resonances, and to control these secondary instabilities using a local wall cooling strip. The results indicate that the nonlinear interaction between the high-amplitude primary mode and low-amplitude secondary modes is the main contributor to transition. The mutual- and self-interactions of the primary and secondary modes generate other harmonic modes with laminar breakdown soon appearing. The asymmetric subharmonic resonance induces the earliest transition, while the fundamental subharmonic has the latest. Wall cooling effects are also studied. The results show that a lower wall temperature significantly suppresses the secondary instabilities, and steady modes become dominant and lead to obvious streamwise vortexes. Numerical data demonstrate that all secondary-instability-induced transitions result in fully developed turbulent boundary layers, as supported by the skin friction and scaled velocity profiles. The transition control cases indicate that the local wall cooling strip can significantly delay the transition by suppressing the growth of the primary mode. An upstream control strip is found to have a more obvious suppression effect. The fundamental and asymmetric subharmonic resonances are sensitive to the location of the local wall cooling strip and show a stronger transition delaying effect.

show abstract

Section: Introductionmentioning

confidence: 99%

Direct numerical simulation of mechanism and control of secondary instability induced transition in a supersonic boundary layer

Liu,

Huang,

Liu

2024

Physics of Fluids

View full text Add to dashboard Cite

show abstract

“…Furthermore, the interaction between the shock wave and boundary layer is universally present in the throat of supersonic intakes [19]. Huang et al [20][21][22][23] used the boundarylayer bleed system to realize a secondary circulating jet for effectively suppressing this phenomenon. To improve the electromagnetic performance of an intake, two methods are effective: coating the duct with low-scattering materials [24] and connecting an S-duct diffuser to increase the reflected number of electromagnetic waves inside [25].…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation of Aerodynamic and Electromagnetic Performances for S-Duct Caret Intake with Boundary-Layer Bleed System

Wang

2023

International Journal of Aerospace Engineering

View full text Add to dashboard Cite

This study presents the numerical results for the aerodynamic and electromagnetic performances of an S-duct caret intake. Using the multilevel fast multipole method (MLFMM) to solve Maxwell equations, the current on the intake surface is calculated, and the radar cross-section (RCS) is analyzed. Moreover, the intake flow field is numerically investigated using the SST k–ω turbulence model to solve the Reynolds-averaged Navier–Stokes equations. Compared to a straight intake, for an S-duct caret intake, the average RCS is lower by 7.65 dB, and the maximum RCS difference value caused by the blade rotation is lower by 6.75 dB. However, the flow capacity deteriorates when the total pressure recovery coefficient decreases by 0.004. Based on the analysis of the aerodynamic and electromagnetic characteristics of different intakes, a double S-duct intake is designed. Compared to a traditional S-duct intake, for the novel intake after model parameter modification, the average RCS is lower by 0.05 dB, and the total pressure distortion (TPD) is lower by 0.18. The analysis of the effects of different boundary-layer bleed systems shows that the symmetrical layout adversely affects the aerodynamic and electromagnetic performances of the S-duct intake, but the unilateral partial layout is beneficial, whose TPD is lower by 0.04 and average RCS is higher by −2.17 dB compared to a straight intake.

show abstract

Characteristics of self-excited shock wave oscillations in a supersonic isolator with exit duct configurations

James

Sethuraman²,

Kim³

2023

Acta Astronautica

View full text Add to dashboard Cite

Investigation on the adaptive control of shock wave/turbulent boundary layer interaction based on the secondary circulation jets

Cited by 18 publications

References 52 publications

Direct numerical simulation of mechanism and control of secondary instability induced transition in a supersonic boundary layer

Direct numerical simulation of mechanism and control of secondary instability induced transition in a supersonic boundary layer

Numerical Investigation of Aerodynamic and Electromagnetic Performances for S-Duct Caret Intake with Boundary-Layer Bleed System

Characteristics of self-excited shock wave oscillations in a supersonic isolator with exit duct configurations

Contact Info

Product

Resources

About