Concept and Objectives:
DeSiReH focuses on both, the numerical design tools and the experimental measurement techniques for cryogenic conditions, with the objective to improve the industrial design process for laminar wings in terms of product quality, efficiency, and development cost reduction. The work focuses on the design of high lift devices. DeSiReH addresses the following quantified objectives which will make a significant contribution to meeting Vision 2020 goals: 1) Reduction of industrial A/C development costs by 5% by reduced and more efficient Wind Tunnel Testing 2) Decrease time-to-market by 5% by improved aerodynamic design turn-around time 3) Improve industrial High-Lift design process efficiency by 15% 4) Reduce A/C drag by 5% by enabling NLF though compatible High-Lift-Design.
To accomplish these objectives the project is planned for a period of 4 years and a budget of 7.6 Mio. Euro. The consortium consists of 6 industry partner, 7 research establishments, 3 universities, 2 small and medium-sized enterprises and the European Transonic Wind tunnel (ETW). Existing and validated high-fidelity numerical tools are composed to an efficient High-Lift design and optimization process chain in WP1. The strategies and tools developed are applied in WP 2 to the aerodynamic design of a high lift system for the future pointing HARLS wing (High Aspect Ratio Low Sweep) with the constraint to maintain Natural Lamiar Flow at cruise to the best possible extend. WP 3 focuses on the improvement of the experimental measurement technique for cryogenic testing. The objectives here are to enhance the measurement accuracy of the results and to generate the capability to apply different important techniques (e.g. transition measurement & deformation measurement). These techniques are finally applied in the ETW at High-Reynolds-Numbers on the HARLS model equipped with the High-Lift-System, designed in WP2. The final assessment of DeSiReH results is done in WP4.
DESIREH Results in brief:
Improved aircraft wing design
Scientists are developing numerical methods and experimental techniques to streamline the design of future aircraft wings. Significant reductions in cost and time are expected to provide a competitive boost to the aircraft industry.
High-lift devices maximise the lift of aircraft, dependent in a complex way on wing shape, angle and speed of flight. As engines continue to become more powerful and aircraft loads and speed increase, high-lift devices have become a necessity for keeping take-off and landing within reasonable speed limits. High-lift systems also play a critical role in overall flight performance. Small changes in lift and drag facilitated by such systems can yield major increases in payload capabilities.
The aerodynamic design of high-lift systems has become an integral part of aircraft design. European scientists aiming to improve the process initiated the ‘Design, simulation and flight Reynolds number testing for advanced high-lift solutions’ (Desireh) project. The EU-funded consortium consists of six industry partners, seven research establishments, three universities, two small and medium-sized enterprises (SMEs) and the European Transonic Windtunnel (ETW).
Together, the partners are developing numerical tools and experimental measurement techniques for very cold (cryogenic) conditions to enhance the industrial design of laminar wings for high-lift capability. In particular, scientists are working toward development of a high-lift system for the future generation Natural Laminar Flow (NLF) High Aspect Ratio Low Sweep (HARLS) wing that has an optimal wing shape for maintaining laminar flow and thus reducing drag.
Scientists have developed algorithms to optimise all phases of flight (take-off, cruising and landing) simultaneously rather than individually, an important step toward a more balanced design process. In addition, they are accelerating the numerical simulation process that will significantly decrease design time given the huge computational load of the complex models. An optimal high-lift wing design has been selected for optimisation and testing. Finally, improvements in the particle image velocimetry (PIV) technique used to measure air flow have been achieved and measurement techniques have been verified for use without modification in wind tunnel tests.
The last project phase will be devoted to final optimisations of numerical algorithms and wing design and subsequent wind tunnel testing. Desireh accomplishments are expected to have an important impact on the aircraft design sector by decreasing industrial development costs and time-to-market while enhancing laminar wing performance.