Perforated Wall in Controlling the Separation Bubble Due to Shock Wave –Boundary Layer Interaction
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K. Raja sekar
und
P. Manigandan
Abstract
The shock wave boundary layer interaction (SWBLI) induced separation bubble formation (SB) and its control has been investigated numerically in the mixed compression type of intake in the scramjet engine. The external compression has occurred due to the three successive oblique shocks formed from the three successive ramps of the forebody with the semi-wedge angle of 7.6, 7.0, and 9.4 respectively. The intake is designed in such a way that all three shocks converge and impinge on the leading edge of the cowl lip for the operating Mach number of 5.0. The numerical simulation is carried out by solving steady, compressible 2-D RANS equations using transitional SST k-ω turbulence model to capture the influence of SWBLI in the performance of supersonic intake. The formation of SB and its control by establishing the perforated wall in its proximity are investigated for three different cases based on the perforation with respect to SSB. Findings of the numerical simulation have concluded that the size of the SB decreases to an acceptable level while establishing the perforation in the entire fore-body wall in the isolator region. The feedback loop established between the upstream and downstream of SB could be a possible reason for reducing its size.
Nomenclature
- ρ
-
Fluid density
- ui
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Velocity components
- p
-
Pressure
- E
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Total energy
- H
-
Total enthalpy
- μ
-
Total viscosity
- μl
-
Laminar viscosity
- μt
-
Turbulent viscosity
- Cf
-
Skin friction coefficient
-
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Local wall shear stress
-
-
Free stream velocity
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© 2019 Walter de Gruyter GmbH, Berlin/Boston
Artikel in diesem Heft
- Frontmatter
- Original Research Articles
- Investigations of Trenched Film Hole Orientation Angle on Film Cooling Effectiveness
- Jet Flow Control Using Semi-Circular Corrugated Tab
- Simulation of Use-Related Multi-Parameter Load Spectrum Based on Principal Component Analysis
- Characterization of Tandem Airfoil Configurations of Axial Compressors
- Research on Suppressing Vibration of Mistuning Cyclic-Periodic Structure
- Research on Power Regulation Schedule Control System for Turboprop Engine
- Enhancement of Full Coverage Film Cooling Effectiveness with Mixed Injection Holes
- CFD Analysis and Experimental Validation of the Flow Field in a Rib Roughed Turbine Internal Cooling Channel
- Perforated Wall in Controlling the Separation Bubble Due to Shock Wave –Boundary Layer Interaction
- Calculating Endogenous and Exogenous Exergy Destruction for an Experimental Turbojet Engine
- One-equation turbulence models applied to practical scramjet inlet
Artikel in diesem Heft
- Frontmatter
- Original Research Articles
- Investigations of Trenched Film Hole Orientation Angle on Film Cooling Effectiveness
- Jet Flow Control Using Semi-Circular Corrugated Tab
- Simulation of Use-Related Multi-Parameter Load Spectrum Based on Principal Component Analysis
- Characterization of Tandem Airfoil Configurations of Axial Compressors
- Research on Suppressing Vibration of Mistuning Cyclic-Periodic Structure
- Research on Power Regulation Schedule Control System for Turboprop Engine
- Enhancement of Full Coverage Film Cooling Effectiveness with Mixed Injection Holes
- CFD Analysis and Experimental Validation of the Flow Field in a Rib Roughed Turbine Internal Cooling Channel
- Perforated Wall in Controlling the Separation Bubble Due to Shock Wave –Boundary Layer Interaction
- Calculating Endogenous and Exogenous Exergy Destruction for an Experimental Turbojet Engine
- One-equation turbulence models applied to practical scramjet inlet
