Large Eddy Simulation of Supersonic Flat Plate Boundary Layer Part II

2002 ◽  
Author(s):  
Hong Yan ◽  
Doyle Knight ◽  
Alexander Zheltovodov
Keyword(s):  
Boundary Layer ◽  
Large Eddy Simulation ◽  
Flat Plate ◽  
Plate Boundary ◽  
Eddy Simulation ◽  
Large Eddy ◽  
Flat Plate Boundary Layer

Large-Eddy Simulation of Supersonic Flat-Plate Boundary Layers Using the Monotonically Integrated Large-Eddy Simulation (MILES) Technique

2002 ◽  
Vol 124 (4) ◽  
pp. 868-875 ◽  
Author(s):  
H. Yan ◽  
D. Knight ◽  
A. A. Zheltovodov
Keyword(s):  
Heat Transfer ◽  
Boundary Layer ◽  
Heat Transfer Coefficient ◽  
Large Eddy Simulation ◽  
Flat Plate ◽  
Boundary Layers ◽  
Plate Boundary ◽  
Navier Stokes ◽  
Eddy Simulation ◽  
Large Eddy

A supersonic flat-plate boundary layer at a Reynolds number of 2×104 based on the inflow boundary layer thickness is investigated at different Mach numbers (M=2.88 and 4) using the monotonically integrated large-eddy simulation (MILES) technique. The inherent numerical dissipation is taken as an implicit subgrid scales (SGS) model to close the Favre-filtered compressible Navier-Stokes (NS) equations. A finite volume method with second-order accuracy in time and space is implemented for the solution of the Navier-Stokes equations on an unstructured grid of tetrahedra. The heat transfer coefficient is predicted by simulating both adiabatic and isothermal cases. The mean flowfield and turbulent stresses are in good agreement with experiment. The relationship between the predicted skin friction coefficient and heat transfer coefficient is in close agreement with the Reynolds analogy factor. The variation of turbulent Prandtl number cross the boundary layer falls within the experimental envelope. These are the first LES predictions of adiabatic and isothermal supersonic flat plate boundary layers using the MILES technique.

Sensitivity Analysis of Heat Transfer in a Honeycomb Acoustic Liner to Inlet Conditions With Large Eddy Simulation

2017 ◽  
Author(s):  
Florent Duchaine
Keyword(s):  
Boundary Layer ◽  
Large Eddy Simulation ◽  
Flat Plate ◽  
Heat Fluxes ◽  
Operating Conditions ◽  
Computational Domain ◽  
Eddy Simulation ◽  
Large Eddy ◽  
Acoustic Liner ◽  
Inlet Conditions

This article presents a parametric numerical study to analyze the sensitivity of wall heat fluxes on an academic acoustic liner to inlet conditions. Large Eddy Simulation (LES) is used to simulate an array of 20 aligned honeycomb cells on a flat plate with 10% porosity characteristic of installed liners. The computational domain is periodic in the span direction comprising 2 honeycomb cells. The operating conditions are representative of cruise with a Mach number of 0.5 at ambient pressure and temperature. Comparisons of heat fluxes obtained on a none perforated flat plate with the honeycomb liner are proposed with different inlet conditions: steady laminar boundary layer profile, turbulence injection and acoustic perturbation injection at different frequencies. Results show that for the operating condition and the boundary layer thickness used, large differences are observed on the first cells of the liners resulting from different transition to turbulence processes. A first important difference exists from laminar and turbulent conditions where turbulent conditions exhibits higher heat fluxes as expected. Then, case pulsed at the resonant frequency of the honeycomb shows higher heat fluxes than other frequencies. Finally, after a given number of cells, the heat fluxes reach an asymptotic behavior at the same level which seems to be controlled by the turbulence generated by the interaction of the flow and the perforations whatever the inlet conditions.

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