Coupled Aerodynamic Technologies for Aircraft Wings
In this research project, two technologies for influencing wing aerodynamics are coupled to best combine their known advantages.
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The overall objective of the joint project CATeW is to investigate a combination of variable camber (VC) and hybrid laminar flow control (HLFC) on the wing of a medium-range aircraft. The focus is on an evaluation of the impact on the overall aircraft and the identification of dependencies between different design parameters. In addition, potentials with regard to fuel efficiency will be identified, especially for the medium-haul market segment. The project consortium consists of two partners who combine competencies from the fields of aircraft design as well as aerodynamic low and high fidelity considerations. A core aspect of the project lies in overall design studies that take into account the interactions between the technologies.
In this context, the ILR is working on aspects of integrating systems for hybrid laminarization as well as for variable camber, taking into account the effects on aircraft preliminary design. The aim is to reduce the friction drag by adjusting the wing camber inflight to the needs of the laminarity. The ILR can rely on existing expertise regarding the integration of hybrid laminar flow control and variable camber within the in-house aircraft design environment MICADO. For aerodynamic evaluation a process exists, which combines a 2D flow solver with a 3D transition prediction module using various transformation rules. In order to maintain the balance between the levels of detail required in the preliminary design, a detailed system design is carried out taking into account the aerodynamic boundary conditions. Within CATeW, the existing expertise is extended to include the evaluation capability of coupling two technologies. In addition, the aerodynamic low-fidelity results will be enhanced by reduced-order models - derived from the high-fidelity results of the project partner. This will allow a detailed consideration of the advantages due to the aerodynamic efficiency increase as well as the disadvantages due to additional system masses and power off-takes on the engine and their effects on the overall aircraft system within a reasonable computing time.
The project is funded by the German Federal Ministry of Economic Affairs and Energy as part of the Federal Aviation Research Programme LuFo VI-1.
- Chair of Aerodynamics and Fluid Mechanics at Technical University of Munich