Bleeding Control for Improving Internal Waverider Inlet Self-Starting ability
-
Zuo Fengyuan
,
Huang Guoping
Abstract
Internal waverider inlets (IWIs) are novel three-dimensional (3D) high-performance inward turning inlets. However, they possess poor self-starting capacity when applied in a fixed-geometry inlet for ramjets. Firstly, this paper presents an analysis of self-starting capacity for IWIs to demonstrate that IWIs face more difficult challenges when used as ramjet inlets than they do as scramjet inlets. Self-starting capacity must be taken into account when designing ramjet inlets. Secondly, the impact of a fluidic control method on a fixed-geometry IWI was studied by numerical simulation of fluid flow. The numerical results show that the fluidic control mechanism improved the self-starting capacity of the IWI at low Mach numbers: the minimum Mach number of self-starting capacity was reduced from M3.8 to M3.2; furthermore, the compression ratio was increased from 29.9 with no fluidic control to 31.9. By analyzing two different groups of fluidic control positions, it was determined that bleeding before the separation bubble has no impact on the IWI self-starting capacity.
Funding statement: This work is supported by national Natural Science Foundation of China (No. 11372134 and No. 51176072). And this work is part of Project KYLX15_0261 supported by Funding of Jiangsu Innovation Program for Graduate Education, the Fundamental Research Funds for the Central Universities.
Acknowledgements
Dr. Valery Sherbaum and inlet team members in the college of Power and Energy of N.U.A.A are gratefully acknowledged for their cooperation.
Nomenclature
- CR
Total geometrical contraction ratio
- CRI
Internal geometrical contraction ratio
- IWI
Internal waverider inlet
- M
Mach number
- P*
Total pressure, Pa
- q(M)
Flux function
- T*
Total temperature, K
- TBCC
Turbine-based combined-circle
- ηKE
Kinetic energy efficiency
- mCX
Ratio of bleeding mass airflow to capture mass airflow
- ϕ
Mass flow capture coefficient
- πe
Pressure ratio of exit section
- σ
Total pressure recovery
- 0
Freestream
- e
Exit properties
- l
Properties before detached shock wave
- s
Properties after detached shock wave
- t
Throat properties
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© 2019 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
- Frontmatter
- Original Research Articles
- Optimization Design and Experimental Study of a Two-disk Rotor System Based on Multi-Island Genetic Algorithm
- Experimental Investigation of the Effect of the Probe Support Tail Structure on the Compressor Cascade Flow Field
- Investigation on Rotor-Labyrinth Seal System with Variable Rotating speed
- Numerical Prediction of Impact of Clearance on Rotordynamic Coefficients for Labyrinth Brush Seal
- CH* Luminance Distribution Application and a One-Dimensional Model of the Supersonic Combustor Heat Release Quantization
- Bleeding Control for Improving Internal Waverider Inlet Self-Starting ability
- Soot Formation and Its Effect in an Aero Gas Turbine Combustor
- Studies on the Effect of Staggering the Rear Rotor in a Counter Rotating Turbine with Respect to Flow and Performance Parameters
- Aerodynamic Performance and Flow Characteristics of an Industrial Centrifugal Blower Volute with Varied Cross-Sectional Shapes/Area Ratios
- CFD Design Study of a Pressure Probe for Centerline Static Pressure Measurement in Supersonic Ejectors
- The Performance of the Self-Supplying Vortex Generator Jets on a High-Speed Compressor Cascade
Articles in the same Issue
- Frontmatter
- Original Research Articles
- Optimization Design and Experimental Study of a Two-disk Rotor System Based on Multi-Island Genetic Algorithm
- Experimental Investigation of the Effect of the Probe Support Tail Structure on the Compressor Cascade Flow Field
- Investigation on Rotor-Labyrinth Seal System with Variable Rotating speed
- Numerical Prediction of Impact of Clearance on Rotordynamic Coefficients for Labyrinth Brush Seal
- CH* Luminance Distribution Application and a One-Dimensional Model of the Supersonic Combustor Heat Release Quantization
- Bleeding Control for Improving Internal Waverider Inlet Self-Starting ability
- Soot Formation and Its Effect in an Aero Gas Turbine Combustor
- Studies on the Effect of Staggering the Rear Rotor in a Counter Rotating Turbine with Respect to Flow and Performance Parameters
- Aerodynamic Performance and Flow Characteristics of an Industrial Centrifugal Blower Volute with Varied Cross-Sectional Shapes/Area Ratios
- CFD Design Study of a Pressure Probe for Centerline Static Pressure Measurement in Supersonic Ejectors
- The Performance of the Self-Supplying Vortex Generator Jets on a High-Speed Compressor Cascade
