The base flow of an axisymmetric generic space launcher model is investigated experimentally by means of particle image velocimetry and dynamic pressure measurements at a Mach number of 0.76 and a Reynolds number of 1.5 × 106, based on the main body diameter. The flow separation at the end of the main body forms a highly dynamic recirculation region with strong pressure fluctuations on the reattaching surface. The time-averaged reattachment on the rear sting is at 1.05 main body diameters downstream of the step. This work investigates the application of passive flow control devices for their potential of reducing the loads on the space launcher’s nozzle. It is shown that rectangular or circular grooves at the end of the main body force enhanced mixing in the separated shear layer, leading to a reduction of the reattachment length of 55%. Additionally, the fluctuations of the reattachment are significantly reduced, which results in lower-pressure fluctuations and thus reduced dynamic loads.
|Number of pages||8|
|Journal||AIAA Journal: devoted to aerospace research and development|
|Publication status||Published - May 2019|
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