Reference number : GC-2017-Q2-00105, amendment number : , agreement type : G, recipient legal name : Hickey, Jean-Pierre (University of Waterloo), recipient country : CA, recipient province : nan, recipient city : Ontario, recipient postal code : nan, program name english : Engage Grants for Universities, program name french : Subventions d'engagement partenarial pour les universités, program purpose english : The intake of aircraft engines is constructed to provide a steady and uniform flow over a wide range of_x000D_
operating conditions. Nacelles are designed to optimize cruise efficiency while meeting the stringent_x000D_
operational requirements at off-design conditions. One of the most critical operating points occurs on the_x000D_
ground with severe crosswinds when the aircraft is at rest. In this setup, the crosswind causes a stagnation point_x000D_
to occur on the outer nacelle, the flow then accelerates and transitions around the lip before entering the engine_x000D_
at a near-sonic speed. The negative pressure gradient at the engine inlet results in flow separation, which_x000D_
distorts the incoming flow stream; at sufficiently large distortion levels, stall or aerodynamic instabilities of the_x000D_
fan blades may arise. The accurate prediction of the engine inflow distortion is extremely difficult as it involves_x000D_
laminar-to-turbulent transition, complex geometry and pressure gradients and flow separation. This project_x000D_
seeks to improve on existing transitional models to accurately determine the onset of transition on a complex_x000D_
three-dimensional nacelle, and thus improve the prediction accuracy of inflow distortion at these critical_x000D_
off-design conditions., program purpose french : The intake of aircraft engines is constructed to provide a steady and uniform flow over a wide range of_x000D_
operating conditions. Nacelles are designed to optimize cruise efficiency while meeting the stringent_x000D_
operational requirements at off-design conditions. One of the most critical operating points occurs on the_x000D_
ground with severe crosswinds when the aircraft is at rest. In this setup, the crosswind causes a stagnation point_x000D_
to occur on the outer nacelle, the flow then accelerates and transitions around the lip before entering the engine_x000D_
at a near-sonic speed. The negative pressure gradient at the engine inlet results in flow separation, which_x000D_
distorts the incoming flow stream; at sufficiently large distortion levels, stall or aerodynamic instabilities of the_x000D_
fan blades may arise. The accurate prediction of the engine inflow distortion is extremely difficult as it involves_x000D_
laminar-to-turbulent transition, complex geometry and pressure gradients and flow separation. This project_x000D_
seeks to improve on existing transitional models to accurately determine the onset of transition on a complex_x000D_
three-dimensional nacelle, and thus improve the prediction accuracy of inflow distortion at these critical_x000D_
off-design conditions., agreement title english : Predictive Modelling of Engine Inlet Distortion in Crosswind Conditions, agreement title french : Predictive Modelling of Engine Inlet Distortion in Crosswind Conditions, agreement number : EGP, agreement value : 25000.0, agreement start date : 2017-07-12, agreement end date : nan, description english : nan, description french : nan, expected results english : nan, expected results french : nan, additional information english : Grant or Award spanning more than one fiscal year (2017-2018 to 2018-2019)., additional information french : Subvention ou bourse octroyée s'appliquant à plus d'un exercice financier (2017-2018 à 2018-2019)., owner organization : nserc-crsng, owner organization title : Natural Sciences and Engineering Research Council of Canada | Conseil de recherches en sciences naturelles et en génie du Canada