초음속 디퓨져에서 발생하는 충격파 진도의 피동제어

DOI QR코드

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김희동;송미일태
Kim, Heuy-Dong;Matsuo, Kazuyasu

  • 발행 : 1996.03.01

초록

Shock wave/boundary layer interaction frequently causes the shock wave to oscillate violently and thus the global flow field to unstabilize. In order to stabilize the shock wave system in the diffuser of a supersonic wind tunnel, the present study attempted to control the shock oscillations by using a passive control. A porous wall with the porosity of 19.6% was mounted on a shallow cavity. Experiment was made by means of schlieren optical observation and wall pressure measurements. The flow Mach number just upstream the shock system and Reynolds number based on the turbulent boundary layer thickness were 2.1 and 1.8 * 10$\^$6/, respectively. The results show that the present passive control method on the shock wave/boundary layer interaction in the supersonic diffuser can significantly suppress the oscillations of shock system, especially when the shock system locates at the porous wall.

키워드

압축성흐름;경계층;간섭;진동;의사충격파;초음속디퓨져;초음속풍동