Mach 6 testing of a scramjet engine model

苅田, 丈士; 齋藤, 俊仁; 工藤, 賢司; 小室, 智幸; 小野, 文衛; Kanda, Takeshi; Saito, Toshihito; Kudo, Kenji; Komuro, Tomoyuki; Ono, Fumiei; Matsui, Atsushi

doi:10.2514/6.1996-380

Cited by 5 publications

(5 citation statements)

References 6 publications

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“…2, 14 Further downstream towards the combustor exit, the reactive flow shows a typical wall pressure distribution of supersonic combustion. 15,16 Upstream of the central injector no influence is observed. This shows a good stability of the inlet and the validity of the additional air injection to impose back-pressure.…”

Section: Flight Condition Reacting-casementioning

confidence: 80%

Experimental and Numerical Investigations of a Scramjet Model Tested in the H2K Blow Down Wind Tunnel at Mach 7 Flight Condition

Riehmer

Rabadan

Gülhan

2014

19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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In the present paper the comparison between experiments and numerical simulations for a generic Scramjet configuration are been presented. The experiments have been conducted for a Mach 7 condition at the hypersonic blow down wind tunnel H2K at the German Aerospace Center (DLR) in Cologne. The corresponding numerical simulations have been performed using two different numerical solvers. During the experiments, air was injected through central strut and wall-ramp injectors to simulate a combustion backpressure. In order to generate a database for a comparison between numerical and experimental data, wall pressures were measured along the bottom and top side walls, Pitot pressure at the exit of the combustor, and heat flux on the sidewalls. The reasonable good agreement between the experiments and the numerical solutions show the feasibility of the numerical tools to predict complex flow structures in high-speed flows. Furthermore, an extrapolation of the numerical and experimental data to real flight conditions at an altitude of 30 km was undertaken and the feasibility of the proposed Scramjet configuration is been shown.

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Section: Flight Condition Reacting-casementioning

confidence: 80%

Experimental and Numerical Investigations of a Scramjet Model Tested in the H2K Blow Down Wind Tunnel at Mach 7 Flight Condition

Riehmer

Rabadan

Gülhan

2014

19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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“…[5][6][7][8][9][10][11][12][13][14][15] In the scramjet engine tests carried out in the RJTF it has been found that the difference of engine inner configuration, mainly strut shape, produces large difference of thrust performance in the condition of Mach 6. 5 In addition to the above it has been also found that the fuel cannot spread all over the engine cross section and concentrates to the top wall side.…”

Section: Japan Aerospace Exploration Agency (Jaxa) Has Been Investigamentioning

confidence: 99%

“…Figure 1 shows the outline of the tested engine. [5][6][7][8][9][10][11][12][13][14][15] The engine is rectangular shape having the overall length of 2.1m, width of 200mm and height of 250mm, and consists of inlet, isolator, combustor and nozzle. The whole of side wall is swept back at 45 degrees to deflect the air stream for spillage required in engine starting.…”

Section: ⅱ．A Tested Enginementioning

confidence: 99%

Virtual Experiment for Optimization of Fuel Distribution in a Scramjet Engine

Sato¹,

Fukui²,

Watanabe³

et al. 2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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Japan Aerospace Exploration Agency (JAXA) has been investigating scramjet engines in KakudaSpace Center using RamJet Engine Test Facility (RJTF) et al. The engine tested at the flight condition of Mach 6 showed very steep fuel distribution. The authors are researching the influence of shock wave from strut-cowl system on the fuel distribution by using CFD based on RJTF tests, and have found advantages of strut in the engine. Here describe the authors the result of virtual experiments for optimization trial of fuel distribution in the engine by means of tracing back along streamlines in the view point where to set the fuel injection positions in order to let the fuel go into high mass flux area in the engine.Ⅰ．Introduction n hypersonic air-breathing engine researches many different trials have been done in order to obtain better propulsion performance or to create new systems. 1-4 In Japan since around 1985 National Aerospace Laboratory (present JAXA) has been carrying out scramjet engine research, and Ramjet Engine Test Facility (RJTF) was built in Kakuda Research Center (present Kakuda Space Center) in 1993 for the research.Kakuda Space Center has been conducting the scramjet engine tests for flight condition of Mach 4, 6, 8 and the higher in RJTF and another facility respectively. [5][6][7][8][9][10][11][12][13][14][15] In the scramjet engine tests carried out in the RJTF it has been found that the difference of engine inner configuration, mainly strut shape, produces large difference of thrust performance in the condition of Mach 6. 5 In addition to the above it has been also found that the fuel cannot spread all over the engine cross section and concentrates to the top wall side. 5 Some fraction of the fuel is exhausted without burning and does not contribute the thrust production. This prevents the engine from fully performing. Optimization for the fuel distribution is needed.In this viewpoint researches have been made on fuel injection for scramjet engines. Roughly classifying, they are a) how I 1 Senior Researcher,

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“…The Ref. [2][3][4][5][6][7][8][9][10][11][12][13][14][15] researched the design method and performance of sidewall inlet in detail.…”

Section: Introductionmentioning

confidence: 99%

Experimental study of three-dimensional sidewall compression inlet designed on wall Mach number linear distribution curved surface compression system

Zou¹,

Zhang²,

Wang³

2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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Three-dimensional sidewall inlet was designed according to curved surface with wall Mach number linear distribution, and obtained curved surface compression sidewall inlet with both topwall and sidewall using curved surface. The inlet was analyzed by numerical simulation and carried out with wind tunnel test. The results show that the inlet's wall pressure distribution changes smoothly under using curved surface, especially having a good performance under off-design condition. Under Ma=6 and zero angle of attack wind tunnel test, curved surface compression sidewall inlet has a total pressure recovery of 0.544, exit Mach number of 2.70, and pressure ratio of 28 relative to wind tunnel static pressure. NomenclatureMa = Mach number H = height p = static pressure T = static temperature P* = total pressure T* = total temperature Φ = flow capture ratio, diameter σ = total pressure recovery π = pressure ratio h = altitude q = dynamic pressure Subscripts ∞ = freestream flow condition throat = throat section of inlet exit = outlet of isolator C = capture 1 Graduate Student,

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Mach 6 testing of a scramjet engine model

Cited by 5 publications

References 6 publications

Experimental and Numerical Investigations of a Scramjet Model Tested in the H2K Blow Down Wind Tunnel at Mach 7 Flight Condition

Experimental and Numerical Investigations of a Scramjet Model Tested in the H2K Blow Down Wind Tunnel at Mach 7 Flight Condition

Virtual Experiment for Optimization of Fuel Distribution in a Scramjet Engine

Experimental study of three-dimensional sidewall compression inlet designed on wall Mach number linear distribution curved surface compression system

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