The utilization of fuel as a heat sink can enable the design of higher-performance aircraft through the reduction of heat loads. A conceptual design phase energy model for the cross section of a wing with an internal fuel tank is developed for computing the rate of heat rejection in flight. The calculations focus on physical dependencies rather than empirical correlations, solving the conservation of energy equation by using results from prior solved conservation of mass and momentum equations. A series of control volumes and various temperature profiles are employed to model the thermal boundary layer. The surface boundary conditions include an isothermal surface as well as an unheated starting length to approximate a heated fuel tank. An implicit root-finding method is verified and used in solving the resulting system of equations. Results are compared to empirical correlations for validation purposes involving laminar and turbulent flow test cases over a flat plate, various NACA airfoils, as well as a C-130 Hercules. Two temperature profiles are considered and compared throughout the verification and validation process. The results show reasonable agreement with empirical correlations, and thus show great promise to be employed in conceptual design.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Wing Fuel-Tank Heat-Sink Calculation for Conceptual Aircraft Design


    Beteiligte:

    Erschienen in:

    Journal of Aircraft ; 54 , 3 ; 1172-1188


    Erscheinungsdatum :

    2017-02-10


    Format / Umfang :

    17 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch






    Wing fuel tank and aircraft

    REN KERONG / WANG WENWEN / QING HUA et al. | Europäisches Patentamt | 2024

    Freier Zugriff

    Aircraft wing fuel tank heat dissipation system and method

    XIE LIANG / LI PENG / HE XUNAN et al. | Europäisches Patentamt | 2023

    Freier Zugriff

    BOX WING AIRCRAFT CONCEPTUAL DESIGN

    Jemitola, P.O. / Fielding, J.P. / International Council of the Aeronautical Sciences; Optimage Ltd | British Library Conference Proceedings | 2012