Boundary layer trip devices for the Hper-X forebody have been experimentally examined in several wind tunnels. Five different trip configurations were compared in three hypersonic facilities, the LaRC 20-Inch Mach 6 Air Tunnel, the LaRC 31 -Inch Mach 10 Air Tunnel, and in the HYPULSE Reflected Shock Tunnel at GASL. Heat transfer distributions, utilizing the phosphor thermography and thin-film techniques, shock system details, and surface streamline patterns were measured on a 0.333-scale model of the Hyper-X forebody. Parametric variations include angles-of-attack of 0-deg, 2-deg, and 4-deg; Reynolds numbers based on model length of 1.2 to 15.4 million: and inlet cowl door simulated in both open and closed positions. Comparisons of transition due to discrete roughness elements have led to the selection of a trip configuration for the Hyper-X Mach 7 flight vehicle.


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    Titel :

    Hypersonic Boundary-Layer Trip Development for Hyper-X


    Beteiligte:

    Kongress:

    18th Applied Aerodynamics Conference ; 2000 ; Denver, CO, United States


    Erscheinungsdatum :

    2000-08-10


    Medientyp :

    Preprint


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Hypersonic Boundary-Layer Trip Development for Hyper-X

    Scott A. Berry / Aaron H. Auslender / Arthur D. Dilley et al. | AIAA | 2001


    Hypersonic boundary-layer trip development for Hyper-X

    Berry, Scott / Auslender, Aaron / Dilley, Arthur et al. | AIAA | 2000


    Hypersonic Boundary-Layer Trip Development for Hyper-X

    S. A. Berry / A. H. Auslender / A. D. Dilley et al. | NTIS | 2000



    Study of Trip-Induced Hypersonic Boundary Layer Transition

    Shrestha, Prakash / Nichols, Joseph W. / Jovanovic, Mihailo R. et al. | AIAA | 2017