Effect of perforated wall in controlling the separation due to SWBLI at Mach no. 5 to 9
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Dinesh Babu R
,
Sunil Chandel
and
Ranjan Kumar Mishra
Abstract
The mixed compression scramjet engine intake was numerically simulated to study the characteristic of shock wave induced boundary layer separation leading to the formation of the separation bubble (SB). The analysis employed a 2D-RANS method with SST k-ω turbulence model at different Mach numbers. The intake is designed as a three-ramp intake for improved performance. As the Mach number varies, the size of the separation bubble formed due to the interaction of oblique shock waves with the boundary layer also varies, affecting both intake the efficiency and overall efficiency of the engine. Apart from traditional control techniques, the most preferred bleed technique is incorporated. Localised & distributed bleed techniques are designed and analysed within the intake at different locations. These techniques result in a reduction in the size of the separation bubble within the intake. Establishing perforation in the engine intake also increases the intake efficiency and overall engine performance.
Nomenclature (SI units)
- μ l
-
laminar viscosity
- μ t
-
turbulent viscosity
- µ
-
total viscosity
- ρ
-
density
- P
-
pressure
- T
-
temperature
- H
-
enthalpy
- γ
-
gamma
-
Research ethics: All research ethics are followed in this work.
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Author contributions: The authors have accepted responsibility for the entire content of this manuscript and approved its submission. Dinesh Babu R. – Meshing, Modelling, CFD Analysis, Writing. Ganapati N. Joshi – Results analysis and writing. Sunil Chandel – Results analysis and writing. Ranjan Kumar Mishra – Results analysis and writing.
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Competing interests: The authors state no conflict of interest.
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Research funding: None declared.
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Data availability: Not applicable.
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© 2024 Walter de Gruyter GmbH, Berlin/Boston
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Articles in the same Issue
- Frontmatter
- Computational analysis of the scramjet mode of the RBCC inlet using micro vortex generators
- Predicting compressor mass flow rate using various machine learning approaches
- Performance analysis of a gas turbine engine with intercooling and regeneration process - Part 1
- Performance analysis of pulse detonation ramjet
- Investigation on flow characteristics and its effect on heat transfer enhancement in a wedge channel with combination of circular, oblong, teardrop, and pencil pin fins
- Effect of perforated wall in controlling the separation due to SWBLI at Mach no. 5 to 9
- Research on performance seeking control of turbofan engine in minimum hot spot temperature mode
- Experimental study on flow field and combustion characteristics of V-gutter and integrated flameholders
- Probabilistic analysis of blade flutter based on particle swarm optimization-deep extremum neural network
- Numerical and experimental study on the critical geometric variation based on sensitivity analysis on a compressor rotor
- Aero-engine direct thrust control based on nonlinear model predictive control with composite predictive model
- Simple model of turbine-based combined cycle propulsion system and smooth mode transition
- Effect of inlet diameter on the flow structure and performance for aluminum-based water-jet engine
- Multi-objective optimization of the aerodynamic performance of butterfly-shaped film cooling holes in rocket thrust chamber
- Application of KH-RT model in lifting flame of methanol jet atomization
- Study of vortex throttle characteristics with adjustable resistance by rotation of the vortex chamber inlet channel
- Enhancing transonic compressor rotor efficiency by flow analysis-driven blade section modification
- Performance analysis of a planar shaped strut injector based supersonic combustion chamber
- The study of cascading effect in the integration of intake with gas turbine engine bay in subsonic cruise vehicle
