Abstract
Large-eddy simulation (LES) of an oblique shock-wave generated by an 8° sharp wedge impinging onto a spatially-developing Mach 2.3 turbulent boundary layer and their interactions has been carried out in this study. The Reynolds number based on the incoming flow property and the boundary layer displacement thickness at the impinging point without shock-wave is 20,000. The detailed numerical approaches are described and the inflow turbulence is generated using the digital filter method to avoid artificial temporal or streamwise periodicity. Numerical results are compared with the available wind tunnel PIV measurements of the same flow conditions. Further LES study on the control of flow separation due to the strong shock-viscous interaction is also conducted by using an active control actuator “SparkJet” concept. The single-pulsed characteristics of the control device are obtained and compared with the experiments. Instantaneous flowfield shows that the “SparkJet” promotes the flow mixing in the boundary layer and enhances its ability to resist the flow separation. The time and spanwise averaged skin friction coefficient distribution demonstrates that the separation bubble length is reduced by maximum 35% with the control exerted.
Highlights
Shock-wave/turbulent boundary layer interaction (SWTBLI) happens ubiquitously in high-speed vehicles, including transonic airfoils, supersonic inlets, control surfaces of aircrafts, missile base flows, reaction control jets, and over-expanded nozzles
The simulation flow condition is consistent with the experiment performed by Dupont et al 42 at IUSTI, i.e. an oblique shock-wave generated by an 8° sharp wedge impinging onto a Mach 2.3 turbulent boundary layer
As we focused on the characteristics of a single-pulse, the pulse frequency is not involved here, the flow field is sampled every 4μs in a time span of 1000μs after energy deposition starts
Summary
Shock-wave/turbulent boundary layer interaction (SWTBLI) happens ubiquitously in high-speed vehicles, including transonic airfoils, supersonic inlets, control surfaces of aircrafts, missile base flows, reaction control jets, and over-expanded nozzles. Among these configurations, maximum mean and fluctuating wall pressure and thermal loads are often found in the vicinity of SWTBLI region and they can cause serious aerodynamic and structural problems.[1] Over the past sixty years, the SWTBLI phenomenon has been investigated over a wide range of configurations and flow conditions. This is an Open Access article published by World Scientific Publishing Company. Further distribution of this work is permitted, provided the original work is properly cited
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