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Grant: Collaborative Research and Development Grants

École Polytechnique de Montréal

$126,000.00

Simulations of icing and transitional flows using RANS modeling around 3D full aircraft configurations

FY 2016-17

Summary
The air transport industry is introducing more and more stringent certification requirements (such as flight into icing conditions) and/or performance enhancement targets (CO2 reductions). This project develops new aerodynamic models in the areas of aero-icing and transitional flows for complex 3D aircraft geometries that can be used by aircraft manufacturers to achieve their design goals.Environmental conditions can lead to formation of ice on the aircraft surfaces, leading to reduced performance that can affect security. Notably during flight into icing atmospheric conditions, the effects of Supercooled Large Droplets on the aircraft's high-lift aerodynamics must be determined. Simultaneously, high-speed laminar flow wings are seen as a possible means of reducing aircraft drag, but three-dimensional flow over swept wings can trigger physical mechanisms that are not apparent in their 2D counterparts (e.g. cross-flow transition from laminar to turbulent regimes). Transition plays an important role in extrapolating wing-tunnel results on high-lift (laminar bubbles) and high-speed (shock waves) flows to flight conditions. The research project thus proposes to develop an aero-icing suite with special care in robust 3D simulations over complex realistic high-lift geometries and 3D transitional turbulence models. Finally, low-fidelity models via a non-linear Vortex Lattice Method will be used to perform trade-offs between icing security margins and fuel reduction gains. Geometrical complexities of high-lift devices (slats or flaps) over complex geometries in icing conditions are treated via the use of unstructured grid techniques, whereas high-speed flows will be solved using the Chimera approach coupled to novel 3D mesh generation techniques on structured grids. This project will train HQP in these areas, as well as high performance computing and source code developments. The final deliverables will benefit the sponsor, Bombardier Aerospace, and the entire Canadian community as aero-icing and transitional flows have impacts on many sectors i.e. wind energy, transport of electricity, etc.
Program
Collaborative Research and Development Grants
Location
Quebec, Canada
Recipient Type
Academia
Type
Grant
Source
NSERC's Awards Data

As published

Application id
488646-2015
Name nom
Laurendeau, Eric
Department département
Génie mécanique
Organization id
64
Institution établissement
École Polytechnique de Montréal
Province en
Québec
Province fr
Québec
Country en
CANADA
Country fr
CANADA
Fiscal year exercice financier
2016
Competition year année de concours
2015
Award amount
126000
Program id
CRDPJ
Program name en
Collaborative Research and Development Grants
Program name fr
Subventions de recherche et développement coopérative
Group en
Research partnerships programs
Group fr
Programmes de partenariat
Committee code
96
Committee name en
RPP Internal Decision Cttee
Committee name fr
Cté de décision interne - PPR
Area of application code
703
Area of application group en
Transportation systems and services
Area of application group fr
Services et systèmes de transport
Area of application en
Aerospace
Area of application fr
Aérospatial
Research subject code
2203
Research subject group en
Fluid mechanics
Research subject group fr
Mécanique des fluides
Research subject en
Modelling, simulation
Research subject fr
Modélisation et simulation
Partie
1
Nb partie
3
Application title
Simulations of icing and transitional flows using RANS modeling around 3D full aircraft configurations
Keyword
NSERC
Application summary
The air transport industry is introducing more and more stringent certification requirements (such as flight into icing conditions) and/or performance enhancement targets (CO2 reductions). This project develops new aerodynamic models in the areas of aero-icing and transitional flows for complex 3D aircraft geometries that can be used by aircraft manufacturers to achieve their design goals.Environmental conditions can lead to formation of ice on the aircraft surfaces, leading to reduced performance that can affect security. Notably during flight into icing atmospheric conditions, the effects of Supercooled Large Droplets on the aircraft's high-lift aerodynamics must be determined. Simultaneously, high-speed laminar flow wings are seen as a possible means of reducing aircraft drag, but three-dimensional flow over swept wings can trigger physical mechanisms that are not apparent in their 2D counterparts (e.g. cross-flow transition from laminar to turbulent regimes). Transition plays an important role in extrapolating wing-tunnel results on high-lift (laminar bubbles) and high-speed (shock waves) flows to flight conditions. The research project thus proposes to develop an aero-icing suite with special care in robust 3D simulations over complex realistic high-lift geometries and 3D transitional turbulence models. Finally, low-fidelity models via a non-linear Vortex Lattice Method will be used to perform trade-offs between icing security margins and fuel reduction gains. Geometrical complexities of high-lift devices (slats or flaps) over complex geometries in icing conditions are treated via the use of unstructured grid techniques, whereas high-speed flows will be solved using the Chimera approach coupled to novel 3D mesh generation techniques on structured grids. This project will train HQP in these areas, as well as high performance computing and source code developments. The final deliverables will benefit the sponsor, Bombardier Aerospace, and the entire Canadian community as aero-icing and transitional flows have impacts on many sectors i.e. wind energy, transport of electricity, etc.