초음속 유체진동기를 이용한 충격파-경계층 박리유동 제어의 비정상성 연구 = Unsteadiness of the Control of Shock-Induced Boundary-Layer Separated Flow Using Supersonic Fluidic Oscillator

국문 초록 (Abstract)

자유유동 마하수 2.4인 초음속 유동에서 형성되는 경사충격파에 의하여 난류경계층이 박리될 수 있다. 이때 박리유동의 제어를 위하여 다양한 유동제어 기술이 적용될 때 나타나는 박리유동의 비정상성 특성변화가 실험적으로 관찰되었다. 경계층의 박리지점 전방에 제트분출을 이용하는 고전적인 제어장치와 최근 개발된 초음속 유체진동기 제어장치가 각각 위치할 때 나타나는 박리기포의 진동특성이 비교 분석되었다. 각 제어장치들의 위치와 제어압력 변화에 따른 후방 경계층 박리유동의 비정상적 특성의 비교를 위하여 고속응답 압력센서 측정과 얻어진 신호에 대한 통계처리 분석기법이 사용되었고, 특정 운용조건에서 유체진동기가 갖는 우수한 제어성능을 확인하였다.

다국어 초록 (Multilingual Abstract)

In supersonic flows with a freestream Mach number of 2.4, the turbulent boundary layer could be separated by an oblique shock wave. The characteristics of the unsteadiness change of the separated flow were experimentally observed when various flow control techniques were applied to control the separated flows. The unsteadiness of the separated flows were analyzed and compared for two different control techniques applied ahead of the separation location; a conventional control technique using supersonic jet ejection and a recently developed supersonic fluidic oscillator. Measurement of high-frequency response pressure guages and statistical analysis of the measured signals were employed to compare the unsteadiness of the separated flows for various locations and control pressures of the control devices, and the fluidic oscillator operated in a specific condition was observed to have favorable control performances.

참고문헌 (Reference)

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