• 제목/요약/키워드: 극초음속(Hypersonic)유동

Search Result 54, Processing Time 0.019 seconds

Numerical Study of Shock Wave-Boundary Layer Interaction in a Curved Flow Path (굽어진 유로 내부의 충격파-경계층 상호작용 수치연구)

  • Kim, Jae-Eun;Jeong, Seung-Min;Choi, Jeong-Yeol;Hwang, Yoojun
    • Journal of the Korean Society of Propulsion Engineers
    • /
    • v.25 no.6
    • /
    • pp.36-44
    • /
    • 2021
  • Numerical analysis was performed on the shock wave-boundary layer interaction generated in the internal flow path of the curved interstage of the scramjet engine flight test vehicle. For numerical analysis, the turbulence model k-ω SST was used in the compressibility Raynolds Averaged Navier Stokes(RANS) equation. Representatively, the separation bubbles on the upper wall of the nozzle, the interaction between the concave shock wave and the boundary layer, and the shock wave-shock wave interaction at the edge were captured. The analysis result visualizes the shock wave-boundary layer interaction of the curved internal flow path to enhance understanding and suggest design considerations.

Ramjet Mode Combustion Test for a Dual-Mode Ramjet Engine Model with a Large Backward-Facing Step (큰 후향 계단이 있는 이중 모드 램젯 엔진 모델의 램젯 모드 연소 시험)

  • Yang, Inyoung;Lee, Kyung-jae;Lee, Yang-ji;Kim, Chun-taek
    • Journal of the Korean Society of Propulsion Engineers
    • /
    • v.20 no.6
    • /
    • pp.83-90
    • /
    • 2016
  • Ramjet mode combustion test was performed for a dual-mode ramjet engine model. The engine model consists of an air intake, a combustor and a nozzle. The combustor in the model has a large backward-facing step, designed to be used as a part of a rocket-based combined cycle engine. The test was performed at the flight speed of Mach 5 and the altitude of 24 km. Strong combustion was established only when the fuel was injected from both of the bottom-side and cowl-side wall. When the total fuel stoichiometric ratio was 1.0, distributed as 0.5 on the cowl side and 0.5 on the bottom side, the flow became subsonic at some portion in the combustor by thermal choking, i.e., ramjet mode was established for this condition.

Characteristics on Combustion Mode in Dual Mode Scramjet Engine (이중모드 스크램제트 엔진의 연소모드 특성)

  • Namkoung, HyuckJoon;Shim, ChangYeul;Kim, SunYong;Lee, MinSoo;Park, JooHyon;Kim, DongHwan
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • 2017.05a
    • /
    • pp.330-335
    • /
    • 2017
  • Recently many studies have been made for the development of propulsion system with wide range flight from supersonic to hypersonic. Dual Mode scramjet engine as a hybrid cycle with advantage of ramjet and scramjet has one combustor. It works under the ramjet mode (subsonic combustion) and scramjet mode (supersonic combustion) respectively. In this study, Experimental results of hot firing tests of dual scramjet engine designed on the condition of Mach 3.5~6 as a flight Mach number are discussed. The tests were carried out on a ground test bench under free stream condition of Mach 6 at 27.6km altitude. In the tests, the adopted design and technological solutions were verified and efficient operation of the dual mode ramjet engine with Kerosene combustion during 5 seconds was demonstrated.

  • PDF

Combustion Test for a Supersonic Combustor Using a Direct-Connected Facility (직결형 설비를 이용한 초음속 연소기 연소 시험)

  • Yang, Inyoung;Lee, Kyung-Jae;Lee, Yang-Ji;Lee, Sanghoon;Kim, Hyungmo;Park, Poomin
    • Journal of the Korean Society of Propulsion Engineers
    • /
    • v.22 no.3
    • /
    • pp.1-7
    • /
    • 2018
  • A combustion test for a supersonic combustor was conducted using a direct-connected type supersonic combustor test facility. The facility was verified for the capability of simulating required flow conditions. The test condition was maintained at Mach 2.0, $915^{\circ}C$ and 496 kPa for 15 s. Using gaseous hydrogen as the fuel, the combustor model was also tested for its ignition and flame holding capability at the fuel equivalence ratio of 0.12. Combustion efficiency was 71%, and the supersonic flow regime was obtained at this test condition.