Study of Correctly Expanded Sonic Jet with Air Tabs
-
Arun Prasad R
,
Sembaruthi M
Abstract
The present numerical study is to understand the effect of air tabs located at the exit of a convergent nozzle on the spreading and mixing characteristics of correctly expanded sonic primary jet. Air tabs used in this study are two secondary jets issuing from constant diameter tubes located diametrically opposite at the periphery of the primary nozzle exit, normal to the primary jet. Two air tabs of Mach numbers 1.0 to 1.4, in steps of 0.1 are considered in this study. The mixing modification caused by air tabs are analysed by considering the mixing of uncontrolled (free) primary jet as a reference. Substantial enhancement in jet mixing is achieved with Mach 1.4 air tabs, which results in 80 % potential core length reduction. The total pressure profiles taken on the plane (YZ) normal to the primary jet axis, at various locations along the primary jet centreline revealed the modification of the jet cross sectional shape by air tabs. The stream-wise vortices and bifurcation of the primary jet caused by air tabs are found to be the mechanism behind the enhanced jet mixing.
Nomenclature
- D
-
Nozzle exit diameter
- d
-
Air tab diameter
- pt
-
Total pressure
- p0
-
Total pressure at nozzle and air tab inlet
- Mc
-
Mach number of Air tab
- NPR
-
Nozzle Pressure Ratio
- X
-
Axis along the primary jet centreline
- Y
-
Axis normal to the air tab
- Z
-
Axis along the air tab
- SST
-
Shear Stress Transport Turbulence Model
- k
-
Turbulence kinetic energy
- ε
-
Rate of dissipation of turbulence energy
- ω
-
Specific rate of dissipation of turbulence energy
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Articles in the same Issue
- Frontmatter
- Original Research Articles
- Novel Closed-Form Equation for Critical Pressure and Optimum Pressure Ratio for Turbojet Engines
- Development of Combustor for a Hybrid Turbofan Engine
- A Parametric Study of Hydrogen Fuel Effects on Exergetic, Exergoeconomic and Exergoenvironmental Cost Performances of an Aircraft Turbojet Engine
- A Model Reference Adaptive Sliding Mode Control Method for Aero-Engine
- Numerical Study of Mixing Enhancement in 2D Supersonic Ejector
- Flow Development Through An S-Shaped Diffusing Duct
- Nozzle Geometry Effect on Twin Jet Flow Characteristics
- Application of Proper Orthogonal Decomposition Method in Unsteady Flow Field Analysis of Axial High Bypass Fan
- A Research on Aero-engine Control Based on Deep Q Learning
- Blade Number Selection for a Splittered Mixed-Flow Compressor Impeller Using Improved Loss Model
- Study of Correctly Expanded Sonic Jet with Air Tabs
- Large-Eddy Simulation of Shaped Hole Film Cooling with the Influence of Cross Flow
- Modal Analysis of the Axial Compressor Blade: Advanced Time-Dependent Electronic Interferometry and Finite Element Method
- Exergy Analysis of a Turboprop Engine at Different Flight Altitude and Speeds Using Novel Consideration
- Thermal Optimization Design of Heat Exchanger in Supersonic Engine with Parameters’ Fluctuation
Articles in the same Issue
- Frontmatter
- Original Research Articles
- Novel Closed-Form Equation for Critical Pressure and Optimum Pressure Ratio for Turbojet Engines
- Development of Combustor for a Hybrid Turbofan Engine
- A Parametric Study of Hydrogen Fuel Effects on Exergetic, Exergoeconomic and Exergoenvironmental Cost Performances of an Aircraft Turbojet Engine
- A Model Reference Adaptive Sliding Mode Control Method for Aero-Engine
- Numerical Study of Mixing Enhancement in 2D Supersonic Ejector
- Flow Development Through An S-Shaped Diffusing Duct
- Nozzle Geometry Effect on Twin Jet Flow Characteristics
- Application of Proper Orthogonal Decomposition Method in Unsteady Flow Field Analysis of Axial High Bypass Fan
- A Research on Aero-engine Control Based on Deep Q Learning
- Blade Number Selection for a Splittered Mixed-Flow Compressor Impeller Using Improved Loss Model
- Study of Correctly Expanded Sonic Jet with Air Tabs
- Large-Eddy Simulation of Shaped Hole Film Cooling with the Influence of Cross Flow
- Modal Analysis of the Axial Compressor Blade: Advanced Time-Dependent Electronic Interferometry and Finite Element Method
- Exergy Analysis of a Turboprop Engine at Different Flight Altitude and Speeds Using Novel Consideration
- Thermal Optimization Design of Heat Exchanger in Supersonic Engine with Parameters’ Fluctuation
