• Title/Summary/Keyword: 초음속 공기흡입구

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Study on the Flow Characteristics of Supersonic Air Intake at Mach 4 (마하4 초음속 공기 흡입구 유동 특성에 관한 연구)

  • ;;;;Shigeru , Aso
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.34 no.10
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    • pp.61-70
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    • 2006
  • A Supersonic air intake model was designed for the high performance ramjet and dual-mode scramjet engine to operate at Mach 4 flight condition. The air intake was tested in the blowdown-type wind tunnel of Kyushu University to identify the internal flow characteristics corresponding to the flight parameters such as the back pressure, angle of attack and angle of yaw. Flow visualization was achieved by the Schlieren and oil flow visualization techniques. The intake performance was analyzed quantitatively based on the surface pressure and total Pressure measurements. The experimental results were compared with the computational fluid dynamics results. The present study exhibits the fundamental but rarely found experimental results of the high Mach number supersonic air intake.

Experimental Study on the Supersonic Air Intake at Mach 4 (마하4 초음속 공기 흡입구 유동 특성에 관한 실험적 연구)

  • Lee Hyoung-Jin;Jeung In-Seuck;Aso Shigeru
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • v.y2005m4
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    • pp.394-398
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    • 2005
  • Ramjet engine have been usually operated on Mach $1.5\sim3$ as the vehicle of supersonic cruising engine and studied about the higher performance above Mach 4. The research of Duel mode Scramjet engine which have duel operating mode of ramjet/Scramjet are in progress actively nowadays. This paper suggests the effect the flow characteristics and the effects of back pressure, angle of attack, angle of yow on the supersonic air intake on mach 4 through the Schlieren/Oil flow visualization, and pressure measurement on experimental model.

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Study on the Buzz Characteristics of Supersonic Air Intake at Mach 2.5 (마하 2.5 초음속 공기흡입구의 버즈 특성에 관한 연구)

  • Lee, Hyoung-Jin;Jeung, In-Seuck
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2006.11a
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    • pp.331-335
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    • 2006
  • Theoretically, stable operations of an inlet are achieved at the design condition. However, at off-design conditions supersonic inlets often encounter the problem of aerodynamic instability, called inlet buzz. During inlet buzz, supersonic inlets exhibit considerable oscillation of the shock system in front of the inlet and corresponding large pressure fluctuations downstream. This phenomenon results in decrease of engine performance. An experimental and numerical study was conducted to investigate the phenomenon of supersonic inlet buzz on a generic, axisymmetric, external-compression inlet with a single-surface center-body. This study suggest that intermittent buzz exist and the frequency become to be large as increasing the back pressure.

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Aerodynamic characteristics of Air Inlet Model for Ramjet Engine Mach Number of 2.2 (Mach2.2 램제트엔진 항공흡입구 모형의 공기역학적 특성)

  • 박종호;신완순;신필권;박용철;김윤곤
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 1998.10a
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    • pp.12-12
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    • 1998
  • 무기체계의 추진체로서 고체 로켓트 추진기관이 제작의 용이성, 구조의 간단성, 이에 따른 저렴한 제작비, 그리고 고 신뢰도 확보가능 등의 여러 장점으로 대부분의 현존 전술 유도무기에 채택되어 사용되어 오고 있으나 대응, 방어 무기체계의 빠른 발전으로 이에 따른 새로운 추진기관의 유도무기체제가 요구되고 있다. 램제트 기관은 공기흡입추진기관으로 상대적으로 높은 비추력(1000-2000s)과 추력 중량비(∼20)을 가지며, 이로 인해 기존의 로켓 엔진에 비해 4-5배의 성능을 낼 수 있으며, 초음속 장거리 비행에 적합하다며, 또한 높은 속도영역까지 운용가능하고 구조가 비교적 간단하다.

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Model and component based modeling and simulation of a supersonic propulsion system (모델 및 구성품 기반 초음속 추진기관 실시간 모델링 및 시뮬레이션)

  • Choi, J.H.;Park, I.S.;Lee, J.Y.;Kim, J.H.;Kim, I.S.;Yoon, H.G.;Lim, J.S.;Kim, C.B.;Park, J.M.
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.11a
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    • pp.579-583
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    • 2011
  • The component based propulsion modeling and simulation of an air-breathing engine such as ramjet and scramjet is studied. The simulation model has been realized considering the characteristics of the air-breathing engine which is composed of air intake, combustor and nozzle including engine controller and fuel supply system. To estimate the engine performance and to verify the engine controller, real time based Hardware in the Loop System simulating actual environment is constructed.

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Study on the Buzz Characteristics of Supersonic Air Intake at Mach 2.5 (마하 2.5 초음속 공기흡입구의 버즈 특성에 관한 연구)

  • Lee, Hyoung-Jin;Park, Tae-Hyoung;Choi, Jeong-Yeol;Jeung, In-Seuck
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.35 no.5
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    • pp.426-437
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    • 2007
  • off-design conditions, supersonic air inlets often encounter the problem of aerodynamic instability, called inlet buzz, which causes the significant degradation of the engine performance. An experimental and numerical study was conducted to investigate the phenomenon of supersonic inlet buzz on a generic, axisymmetric, external-compression inlet with a single-surface center-body. It is understood the mechanism of buzz onset as proving that the origin of buzz is the flow choking induced by separation at the intake throat. Also it is observed the intermittent and continuous buzz mode as area ratio varies and understood the transition process through this study. The buzz frequency become to be higher as decreasing the area ratio, but for each area ratio, the frequency of pressure oscillation is the same at all points of intake.

The Study of Aerodynamic Characteristics of Ram-jet with Different Intake (서로 다른 램제트 흡입구에 따른 공기역학적 특성 연구)

  • Park, Soon-Jong;Park, Jong-Ho
    • Journal of the Korean Society of Propulsion Engineers
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    • v.14 no.6
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    • pp.9-16
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    • 2010
  • The SFRJ(Solid Fuel Ram-Jet) propulsion is attractive for projectiles because of the combination of high propulsive performance and low system complexity more than conventional projectiles. The Objective of this research was to characterize the inlet aerodynamic characteristics (center-body & pitot type) in SFRJ. Diffuser static pressure & combustion chamber pressure was tested and the AoA was changed $0^{\circ}$ and $4^{\circ}$ at Mach number of 3.0 for performance estimate. The performance study of inlet was carried out with the Schlieren system and Supersonic cold-flow system. Under mach 3.0, the center-body showed twice higher total pressure recovering ratio than the pitot type. A Computational fluid dynamic solution is applied internal flow of inlet and the solutions are compared with experimental results.

Preliminary Design of Movable Ramjet Intake (가변 초음속 흡입구 기본설계)

  • Lee, Kyung-Jae;Kang, Sang-Hun;Lee, Yang-Ji;Yang, Soo-Seok
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2008.05a
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    • pp.207-210
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    • 2008
  • In this study, one type of ramjet intake were designed for the flight condition of Mach number 4 and numerical analysis was performed. In order to widen the flight envelope range (Mach number $2{\sim}6$), movable intake concept was applied. The central body was designed so that the capture area ratio which is one of most important factors of ramjet intake design could be adjusted. And various types of cowl and movable insert part of shell were designed in order to control throat area which could increase total pressure recovery. The numerical results showed that the designed ramjet intake could be applied in various flights Mach number.

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