Our news editors obtained a quote from the research from German Aerospace Center, "Experiments have therefore been carried out with an inlet without and with boundary-layer bleed at an angle of attack of 0 deg and at Mach numbers ranging from 2.5 to 3.5 in the Trisonic Wind Tunnel Cologne. The inlet flow was analyzed with schlieren images and unsteady pressure recordings, where different pressure fluctuations are detected."
According to the news editors, the research concluded: "The results show that the inlet flow is highly unsteady even at supercritical condition and that the subsequently added boundary-layer bleed permits better pressure recovery and a delay in inlet buzzing."
For more information on this research see: Pressure Fluctuations (Buzzing) and Inlet Performance of an Airbreathing Missile.
The news editors report that additional information may be obtained by contacting
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