Asymmetrical Flow Simulation of Icing Effects in S-Duct Inlets at Angle of Attack
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Wonjin Jin
Abstract
The effect of flow angularity on an S-duct inlet with icing is computationally investigated. Flow angularity is simulated through angle-of-attack, and sideslip in addition to asymmetrical ice accretion on the inlet lip. A commercial CFD code, STAR-CCM+ is used for the steadystate computations with the shear-stress transport (SST) k-ω turbulence model. Symmetrical and asymmetrical glaze ice shapes are computationally simulated on the inlet lip. The symmetrical glaze ice uniformly covers the entire cowl lip; whereas the asymmetrical glaze ice is simulated on a 1/4 sector of the inlet lip and is positioned on top, bottom or side of the inlet lip. The results indicate that flow angularity, whether in angle-of-attack or sideslip, aggravates the low performance of inlets with icing. The total pressure recovery suffers an additional ~2% loss and the inlet mass flow rate drops by ~7% when the inlet is at +20° angle of attack, as compared to zero angle, for flight Mach number of 0.34. The extent of loss in total pressure and a drop in mass flow rate depends on the asymmetrical icing location as well as the inlet angle-of-attack and sideslip. In addition, the ice-induced flow blockage is identified as a critical inlet performance parameter, since the symmetrical (360°) glaze ice with its wider flow blockage creates a lower total pressure recovery than the asymmetrical (90°) glaze ice at all angles of attack or sideslip.
Copyright © 2011 De Gruyter
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- GUI Type Fault Diagnostic Program for a Turboshaft Engine Using Fuzzy and Neural Networks
- Numerical Modeling of an Axisymmetric Trapped Vortex Combustor
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- Control of Base Flows with Micro Jets
- Analysis on Cavitation Characteristics of Flow in a Francis Turbine with Different Content of Non-Condensable Gas
- Research on the Optimum Clocking Position in Axial-Flow Turbomachinery
- Asymmetrical Flow Simulation of Icing Effects in S-Duct Inlets at Angle of Attack
- Experimental Investigation of a Twin Fluid Atomizer Spray Using a Diode Laser Based Optical Patternator
Articles in the same Issue
- Future Jet Technologies. Part A. Air, Land and Marine Applications of Thrust Vectoring
- Aerodynamic Characteristics of Three-Dimensional Surface-Mounted Objects in Tandem Arrangement
- GUI Type Fault Diagnostic Program for a Turboshaft Engine Using Fuzzy and Neural Networks
- Numerical Modeling of an Axisymmetric Trapped Vortex Combustor
- Optimization of a Francis Turbine Through Flow Simulation with a RNG k-ω Turbulence Model
- Control of Base Flows with Micro Jets
- Analysis on Cavitation Characteristics of Flow in a Francis Turbine with Different Content of Non-Condensable Gas
- Research on the Optimum Clocking Position in Axial-Flow Turbomachinery
- Asymmetrical Flow Simulation of Icing Effects in S-Duct Inlets at Angle of Attack
- Experimental Investigation of a Twin Fluid Atomizer Spray Using a Diode Laser Based Optical Patternator
