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An Experimental Study on the Improvement of Aerodynamic Characteristics Using the Blowing for RLV
Shigeki TSUCHIYA,Shigeru ASO,Yasuhiro TANI 한국항공우주학회 2008 한국항공우주학회 학술발표회 논문집 Vol.- No.-
To improve the aerodynamic characteristics of Reusable Launch Vehicles (RLV), active flow control methods with blowing were investigated. The testing models are wing body and lifting body contigurations. The experiments have been conducted in low-speed wind tunnels of Kyushu University and transonic wind tunnel of ISAS (Institute of Space and Astronautical Science), JAXA (Japan Aerospace Exploration Agency). For the active flow control, the blowing along the fuselage surface was chosen. Flow visualization results show that the vortex on the fuselage is greatly moved near the fuselage, and the vortex core of the wing is clearly observed. The aerodynamic characteristics result shows that the blowing increases the lift and lift-to-drag ratio. From those results, we confirmed that the blowing can be useful for the improvement of aerodynamic characteristics of the RLV.
Numerical Study on Supersonic Mixing Enhancement with a Ramp Injector and a Cavity
Fumihiko NISHIMOTO,Kohei YAMAGUCHI,Shigeru ASO,Yasuhiro TANI 한국항공우주학회 2008 한국항공우주학회 학술발표회 논문집 Vol.- No.-
In the present study, supersonic mixing enhancement has been investigated computationally for a SCRAM-jet engine model combustor with a swept ramp injector and a cavity. The calculation condition of the main stream are Ma = 3.96, total pressure 1.27 MPa and total temperature 283 K. In order to enhance the mixing among fuel and air a cavity is placed downstream of the ramp injector. The position and geometry of the cavity plays an important role in mixing efficiency. Therefore L/D and the Length from the ramp to the cavity have been varied. From numerical results. the mixing efficiency was the highest when L/D =2, but the total pressure loss was also the highest compared to L/D= 1,3 and 4.
이형진(Hyoung-Jin Lee),김성돈(Sung-Don Kim),정인석(In-Seuck Jeung),최정열(Jeong-Yeol Choi),Shigeru Aso 한국항공우주학회 2006 韓國航空宇宙學會誌 Vol.34 No.10
마하 4 비행 조건에서 작동하는 고성능 램제트와 듀얼모드 스크램제트 엔진의 초음속 공기 흡입구 모델을 설계하였다. 배압, 받음각, 요각 등 비행 변수의 변화에 따른 내부 유동 특성을 파악하기 위하여 규슈대학교의 불어내기식 초음속 풍동을 이용한 실험을 수행 하였다. 유동 가시화를 위하여 쉴리렌 기법, 오일 가시화 기법을 이용하였으며, 정량적 성능 분석을 위하여 표면 압력 및 전압력을 측정하였다. 실험의 결과는 전산 유체 해석과 비교하였다. 본 연구는 기본적이지만 찾기 힘든 고 마하수 초음속 공기 흡입구 유동의 실험 결과를 제시한다. 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.