This thesis deals with preliminary overall aircraft design including hybrid laminar flow control (HLFC) on wings and tails. An integrated methodology and software framework is developed that closes the gap between conceptual aircraft design capabilities and the detailed design tasks of HLFC aerodynamic wing design and HLFC system sizing. The key new achievement of the proposed approach compared to the current state of the art is its capability to perform overall aircraft design studies, while simultaneously capturing the specific influences of different transition mechanisms and transonic drag on swept-tapered wings, as well as the integration of the suction system into the wing.The "Multidisciplinary Integrated Conceptual Aircraft Design and Optimization" (MICADO) framework constitutes the basis for this integrated approach. MICADO consists of a consistent and flexible software architecture, a requirement-driven overall design philosophy, and several loosely-coupled program modules. Most significant elements for HLFC aircraft design are a thermodynamic engine model including secondary power extraction, overall-aircraft drag and mass prediction, and detailed mission performance simulation.The incorporation of HLFC aerodynamics into overall aircraft design is solved by a quasi-three-dimensional wing design approach, and a database containing multi-point optimized HLFC airfoils at different design conditions. An Euler/boundary-layer and a transition prediction code (including cross-flow instabilities) are combined with appropriate sweep-taper transformations into an iterative and robust drag prediction method for transonic HLFC wings. Both pressure and suction distributions are taken into account for automated estimation of power requirements and component masses of the suction system. Applicability and validity of the proposed HLFC aircraft design approach are demonstrated for a long range passenger aircraft. Influences of mass snowball effect, component resizing, and conservative fuel planning for in-flight loss of laminarity are quantified in terms of block fuel and other key design parameters. The significant fuel saving potential of HLFC is confirmed, and further exploited by the integrated design and optimization of HLFC wing geometries for maximum overall aircraft benefit.


    Access

    Download

    Check availability in my library


    Export, share and cite



    Title :

    Preliminary overall aircraft design with hybrid laminar flow control


    Additional title:

    Vorentwurf von Flugzeugen mit hybrider laminarer Strömungskontrolle


    Contributors:

    Publication date :

    2016-01-01


    Size :

    XXX, 200 Seiten : Illustrationen, Diagramme pages


    Remarks:

    RWTH Aachen University, Diss., 2016; Berichte aus der Luft- und Raumfahrttechnik XXX, 200 Seiten : Illustrationen, Diagramme(2016).



    Type of media :

    Miscellaneous


    Type of material :

    Electronic Resource


    Language :

    English




    Conceptual aircraft design with hybrid laminar flow control

    Risse, Kristof / Stumpf, Eike | Online Contents | 2014



    Conceptual aircraft design with hybrid laminar flow control

    Risse, Kristof / Stumpf, Eike | Springer Verlag | 2014


    COMBINED APPLICATION OF HYBRID LAMINAR FLOW CONTROL AND VARIABLE CAMBER IN PRELIMINARY AIRCRAFT DESIGN

    Effing, T. / Schmitz, V. / Shcultke, F. et al. | British Library Conference Proceedings | 2022


    Combined Application of Hybrid Laminar Flow Control and Variable Camber in Preliminary Aircraft Design

    Effing, Tim / Schmitz, Victoria / Schültke, Florian et al. | DataCite | 2022