한국추진공학회지 (Journal of the Korean Society of Propulsion Engineers)

  • 제26권4호
  • /
  • Pages.10-20
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  • 2022
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  • 1226-6027(pISSN)
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  • 2288-4548(eISSN)
한국추진공학회 (The Korean Society of Propulsion Engineers)
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자유제트형 지상추진 시험설비를 사용한 스크램제트 엔진 흡입구의 마하 5 성능시험

Mach 5 Performance Tests of Scramjet Engine Intake Using Free-jet Type Ground Propulsion Test Facility

  • Lee, Yang Ji (Aeropropulsion Research Division, Korea Aerospace Research Institute) ;
  • Yang, Inyoung (Aeropropulsion Research Division, Korea Aerospace Research Institute) ;
  • Lee, Kyung Jae (Aeropropulsion Research Division, Korea Aerospace Research Institute) ;
  • Oh, Jung Hwan (Aeropropulsion Research Division, Korea Aerospace Research Institute) ;
  • Choi, Jin (The 3rd Missile System PMO, Agency for Defense Development)
  • 투고 : 2022.05.30
  • 심사 : 2022.07.23
  • 발행 : 2022.08.31
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초록

한국항공우주연구원의 자유제트형 지상추진시험설비인 스크램제트 엔진 시험설비의 마하 5 조건에서 스크램제트 엔진 흡입구의 성능분석 시험을 진행하였다. 스크램제트 엔진 흡입구의 대표적인 성능 인자인 전압력 회복률, 공기 포획율 측정을 위하여 격리부 후방에 설치되는 피토/정압 레이크가 설계 제작되었다. 격리부 후방에 장착된 레이크가 전방의 흡입구 램프와 격리부에 미치는 영향과 레이크로 측정된 흡입구의 성능 인자 분석 그리고 흡입구의 받음각 변화에 따른 벽면 정압력 분포 변화에 대한 분석이 수행되었다. 끝으로 연소기에서의 압력 상승을 모사하는 장치인 흡입구 후방 배압 조정 장치를 이용하여 흡입구 불시동이 발생하는 시점을 확인하였으며, 본 논문에는 그 결과를 정리하였다.

The performance analysis test of the scramjet engine intake was conducted under the Mach 5 condition of the scramjet engine test facility, a free-jet ground test facility of the Korea Aerospace Research Institute. A pitot/static pressure rake installed at the rear of the isolator was designed and manufactured to measure the total pressure recovery rate and mass capture ratio, which are typical performance factors of the scramjet engine intake. The effect of the rake mounted at the rear of the isolator on the intake, the performance analysis measured by the rake, and the change in wall static pressure distribution according to the angle of attack were performed. Finally, the point at which the intake unstart occurred was confirmed by using the rear back pressure adjusting device, which simulates pressure rise in the combustor, and the results are summarized in this paper.

키워드

과제정보

본 논문은 방위사업청과 국방과학연구소로부터 지원받은 '복합영역 경계층 제어기술'과제의 연구 결과물입니다.

참고문헌

  1. Sanders, B.W. and Weir, L.J., "Aerodynamic Design of a Dual-Flow Mach 7 Hypersonic Inlet System for a Turbine-Based Combined-Cycle Hypersonic Propulsion," NASA CR-215214, 2008.
  2. Slater, J.W. and Saunders, J.D., "Computational Fluid Dynamics (CFD) Simulation of Hypersonic Turbine-Based Combined-Cycle (TBCC) Inlet Mode Transition," 16th International Space Planes and Hypersonic Systems and Technologies Conference, Bremen, Germany, AIAA 2009-7349, Oct. 2009.
  3. Vance, F.D.III, "Computational Analyses of the LIMX TBCC Inlet High-Speed Flowpath," NASA TM-217219, 2012.
  4. Mitani, T., Sakuranaka, N., Tomioka, S. and Kobayashi, K., "Boundary-Layer Control in Mach 4 and Mach 5 Scramjet Engines," Journal of Propulsion and Power, Vol. 21, No. 4, pp. 636-641. 2005. https://doi.org/10.2514/1.7978
  5. Chang, J., Yu, D., Bao, W., Fan, Y. and Shen, Y., "Effects of boundary-layers bleeding on unstart/restart characteristics of hypersonic inlets," The AERONAUTICAL JOURNAL, Vol. 113, No. 1143, pp. 319-327, 2009. https://doi.org/10.1017/S0001924000002992
  6. Herrmann, D., Blem, S. and Gulhan, A., "Experimental Study of Boundary-Layer Bleed Impact on Ramjet Inlet Performance," Journal of Propulsion and Power, Vol. 27, No. 6, pp. 1186-1195, 2011. https://doi.org/10.2514/1.B34223
  7. Ruban, A., Menezes, V. and Balasubramanian, S., "Boundary-Layer Control for Effective Hypersonic Intake," Journal of Propulsion and Power, Vol. 34, No. 6, pp. 1611-1614, 2018.
  8. Verma, S.B., Manisancar, C. and Raju, C., "Control of shock unsteadiness in shock boundary-layer interaction on a compression corner using mechanical vortex generators," Shock Waves, Vol. 50, No. 12, pp. 327-339, 2012. https://doi.org/10.1007/s00193-012-0369-8
  9. Lee, Y.J., Yang, I.Y., Lee, K.J., Oh, J.H. and Choi, J., "Mach 5 Performance Verification of Free-jet type Ground Propulsion Test Facility for Scramjet Engine Intake Test," Journal of the Korean Society of Propulsion Engineers, Vol. 26, No. 1, pp. 77-87, 2022. https://doi.org/10.6108/KSPE.2022.26.1.077
  10. Kantrowitz, A., "The formation and stability of normal shock waves in channel flows," NACA Tech. Note 1225, 1947.
  11. Kantrowitz, A. and Donaldson, C.., "Preliminary investigation of supersonic diffusers," NACA Report L5D20, 1945.
  12. Lee, Y.J., Lee, S.H., Yang, I.Y. and Choi, Y.J., "Rake Design and Test Evaluation for Scramjet Engine Intake Inflow Measurement," 55th KSPE Fall Conference, Busan, Korea, p. 1, Nov. 2020.