This paper continues analysis of data acquired in a series of supersonic crossflow transition experiments on a 65° swept- wing model tested in both wind tunnel and flight. Flow visualization data are summarized to provide context for the swept-wing instability mechanisms of interest. Unsteady pressure measurements obtained near the wing model leading edge (LE) are studied using 2nd- and 3rd-order statistical methods to extract traveling crossflow wave characteristics from these data. Comparisons between tunnel and flight data with boundary-layer (BL) Linear Stability Theory (LST) predictions provide insights into BL transition phenomena similarities and differences observed in tests using the same swept-wing model configurations. Comparisons of unsteady pressure data results for wing LE configurations with and without distributed-roughness-element (DRE) patterns installed, suggest traveling crossflow disturbance growth is reduced when this type of flow control is applied. A brief stud y of different background surface roughness levels on the wing LE suggests the potential for another flow control approach to promote laminar flow on swept wings using streamwise-biased surface finishes.


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    Titel :

    Supersonic Traveling Crossflow Wave Characteristics in Ground and Flight Tests


    Beteiligte:
    Lewis R Owens (Autor:in) / George B Beeler (Autor:in) / Rudolph A King (Autor:in) / Amanda Chou (Autor:in) / Ponnampalam Balakumar (Autor:in) / Daniel W Banks (Autor:in)

    Kongress:

    AIAA SciTech 2020 ; 2020 ; Orlando, FL, US


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch




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    Supersonic Crossflow Transition Control in Ground and Flight Tests

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