Effect of streamwise slots on the drag of a transonic projectile

A. Ibrahim, A. Filippone

    Research output: Contribution to journalArticlepeer-review


    Streamwise slote have been applied to a projectile at transonic speeds as a passive method for controlling normal shock wave/turbulent boundary-layer interaction. The slots are cut on the cylindrical and boattail skins, where shock waves are formed. This study aimed to investigate the effects of the slots on the drag at Mach numbers ranging from 0.85 to 1.10. Investigation of the suction and blowing mechanism through the slots showed a trend similar to a porous surface applied to the area of flow control. This type of control transforms the normal shock wave into a weaker lambda shock structure. Moreover, it produces a thicker boundary-layer profile along and downstream of the slots compared to the baseline boundary layer of a solid wall. Investigation of the flow pattern at a Mach number of 0.96 shows two opposite streamwise circulation vortex pairs: a vortex over the slot surface on the blowing region, and another inside the cavity at the suction region. Finally, a single vortex normal to the freestream direction is formed inside the cavity in the blowing region.
    Original languageEnglish
    Pages (from-to)1865-1876
    Number of pages11
    JournalJournal of Aircraft
    Issue number6
    Publication statusPublished - Nov 2007


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