TEAMAero · Towards Effective Flow Control and Mitigation of Shock Effects in Aeronautical Applications

Towards Effective Flow Control and Mitigation of Shock Effects in Aeronautical Applications

Europe’s future in aviation is closely tied to the goals of Flightpath 2050 – Europe’s Vision for Aviation, an EU report from the HighLevel Group on Aviation Research. These goals include a 75% reduction in CO2 emissions per passenger kilometre to support the Air Transport Action Group target , a 90% reduction in NOx emissions, and noise emissions reduced by 65%. "The aviation industry is entering an era of new technology that will bring a new generation of intelligent aircraft in the market. The new generation of airliners will allow longer maintenance intervals and repair changes as well as better health monitoring and prognostics of maintenance needs." Achieving goals defined in Flightpath 2050 – Europe’s Vision for Aviation will require major improvements in efficiency, which for aircraft means reduced weight and better aerodynamic performance, based on high-performance wings, control surfaces and turbomachinery blades, where transonic ow is common place and the formation of shock waves is the key aerodynamic challenge. In particular, the interaction of shock waves with boundary layers is the primary performance-limiting factor across all of these ow fields. Thus, knowledge of the interaction of shock waves with boundary layer is essential for the development of more efficient aircraft and engines. The problem is that increased aerodynamic forces can lead to flow separation and reductions in engine and airframe efficiency. In such cases, flow control is needed to maintain the system’s performance. Novel designs can also increase the extent of laminar flow and this means that ow-control devices need to operate in a laminar or transitional regime, which requires a better understanding of their function and their interaction with flow transition. Of course, improvements to their effectiveness will have a direct and positive impact on airframe and engine performance. It is because these modern geometries are increasingly complex that we have to really understand and so be able to control three-dimensional flows, especially the three-dimensional shock wave boundary layer interactions (SBLI) The TEAMAero project has the following objectives: (1) to improve our fundamental understanding of the physics of Shock Wave Boundary Layer Interaction (SBLI), including three-dimensionality and unsteadiness; (2) to identify the flow domains best suited to flow-control device installation; (3) to develop flow control methods using wall transpiration, vortex generators and surface treatments to delay the onset of separation or to control shock oscillations, and (4) to develop novel numerical methods for predicting the effects of SBLI.

Текст от CORDIS, на английски · Данни: CORDIS, © Европейски съюз