A theoretical study of the use of heat pipe structures for cooling the leading edges of hypersonic cruise aircraft was carried out over a Mach number range of 6 to 12. Preliminary design studies showed that a heat pipe cooling structure with a 33-in. chordwise length could maintain the maximum temperature of a 65 deg sweepback wing with a 0.5-in. leading edge radius below 1600 F during cruise at Mach 8. A few relatively minor changes in the steady-state design of the structure were found necessary to insure satisfactory cooling during the climb to cruise speed and altitude. It was concluded that heat pipe cooling is an attractive, feasible technique for limiting leading edge temperatures of hypersonic cruise aircraft.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    A feasibility study of heat-pipe-cooled leading edges for hypersonic cruise aircraft


    Contributors:

    Publication date :

    1971-11-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English






    Feasibility of metallic structural heat pipes as sharp leading edges for hypersonic vehicles

    Steeves, Craig A. / He, Ming Y. / Kasen, Scott D. et al. | Tema Archive | 2009


    Dust Erosion Correlation for Mars Entry Vehicles and Hypersonic Cruise Vehicle Leading-Edges

    Boland, Adam J. / Hinkle, Andrew / Hosder, Serhat et al. | AIAA | 2023


    Parametric Geometry Models for Hypersonic Aircraft Components: Blunt Leading Edges

    Kontogiannis, Konstantinos / Cerminara, Adriano / Taylor, Nigel J. et al. | AIAA | 2015