Takeshi Kanda

Chubu University

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Kenji Kudo

Toyota Central Research and Development Laboratories (Japan)

Kouichiro Tani

Japan Aerospace Exploration Agency

Atsuo Murakami

Japan Aerospace Exploration Agency

Sadatake Tomioka

Japan Aerospace Exploration Agency

Tohru Mitani

Japan Aerospace Exploration Agency

Tetsuo Hiraiwa

Japan Aerospace Exploration Agency

Yoshio Wakamatsu

Japan Aerospace Exploration Agency

Nobuo Chinzei

Japan Aerospace Exploration Agency

Goro Masuya

Tohoku University

Kanenori Kato

Japan Aerospace Exploration Agency

Cooperative Institutions

Japan Aerospace Exploration Agency

Chubu University

Tohoku University

Netherlands Aerospace Centre

The University of Tokyo

Osaka University

Waseda University

University of Tsukuba

Kyoto University

Keio University

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Modified Water-Cooled Scramjet Engine Tested under M8 Flight Condition.

JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES (2003)

Kan Kobayashi Sadatake Tomioka Takeshi Kanda Tetsuo Hiraiwa Fumiei Ono

A modified sidewall-compression-type scramjet engine was tested under M8 flight condition. A strut with a long tail led to a 60% higher maximum thrust increment than a strut with a truncated tail, while allowable fuel flow rate (i.e., the flow rate at engine unstart limit) was almost identical. To increase the allowable fuel flow rate and the maximum thrust increment due to combustion without engine unstart, distributed injection in vertical direction and installation of ramps in the isolator between the inlet and the combustor were applied. Distributed fuel injection led to a 30% higher maximum thrust increment than the uniform fuel injection, and the installation of the ramps also gave a 30% higher one than that in the engine without ramp. Gas-sampling at the exit of the engine with distributed fuel injection showed 88% of bulk combustion efficiency. Specific impulses of the maximum thrust increments, δIsp , of the modified engine were 60–80% higher than that of the original engine.

10.2322/jjsass.51.71

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Citations (7)

Effect of Inflow Boundary Layer Thickness on Scramjet Inlet Flowfields.

The Journal of the Japan Society of Aeronautical Engineering (1997)

Masatoshi Kodera Kazuhiro Nakahashi Shigeru Obayashi Takeshi Kanda Tohru Mitani

Flowfields about a scramjet inlet model were numerically simulated by the Thin-Layer Navier-Stokes equations, and effect of inflow boundary layer thickness was investigated. The computations were conducted for inflow Mach number of 3.4. Although pressure at the throat region is relatively constant for various boundary layer thickness, corresponding flow pattern near the top wall was very different to each other, and the total pressure recovery decreased with the boundary layer thickness. The spilled impulse function increased with the thickness of inflow boundary layer, and stream thrust function of the spilled air slightly increased with the boundary layer thickness. The tendency was due to the increase of the separating region with the boundary layer thickness.

Inflow

Scramjet

Boundary layer suction

Specific impulse

Adverse pressure gradient

External flow

Total pressure

10.2322/jjsass1969.45.216

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Citations (1)

Experimental Investigation of an Ejector-Jet

41st Aerospace Sciences Meeting and Exhibit (2003)

Shigeki Aoki Jongsun Lee Goro Masuya Takeshi Kanda Kenji Kudo

10.2514/6.2003-188

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Citations (6)

Mach 6 Testing of a Scramjet Engine Model

Journal of Propulsion and Power (1997)

Takeshi Kanda Tetsuo Hiraiwa Tohru Mitani Sadatake Tomioka Nobuo Chinzei

Testing of a subscale scramjet research engine model was carried out in the Mach 6 Ramjet Engine Test Facility of the National Aerospace Laboratory, Kakuda Research Center. The engine had a sidewall compression-type inlet. The fuel was hydrogen. With the attachment of a short strut on the top wall, intensive combustion with high-combustion efe ciency was attained, and the engine-produced thrust canceled the drag. The e ame was held in the low-velocity region around the step, even after the ignitors had been turned off. When the fuel e ow rate was small, there was a different combustion mode with weak combustion and little thrust. The unstart condition seemed to begin around the cowl. Tangential injection of fuel inhibited intensive combustion.

Ramjet

Scramjet

10.2514/2.5201

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Citations (94)

Experimental studies of supersonic film cooling with shock wave interaction. II

Journal of Thermophysics and Heat Transfer (1997)

M. L. Rightley Takeshi Kanda Fumiei Ono

Choked flow

10.2514/3.942

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Citations (2)

Effects of Deep Throttling on Rocket Engine Systems

Toshiya Kimura Masaki Sato Tadashi Masuoka Takeshi Kanda Atsushi Osada

Dependencies of injection pressure, injection velocity ratio, pump flow rate, and coolant physical condition at a cooling jacket on the engine thrust level were investigated quantitatively for typical rocket engine cycles, an expander-bleed cycle and a staged combustion cycle using a dynamic simulator for a rocket engine. For low injection pressure of oxygen in the expander-bleed cycle engine during deep throttling, the effect of gasification of the oxygen using a heat exchanger was examined numerically. We found that placement of the heat exchanger upstream of the oxygen injector would be effective to increase the injection pressure difference, even though some oscillation would occur.

Bandwidth throttling

Rocket engine

Rocket (weapon)

Liquid-propellant rocket

10.2514/6.2010-6727

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Citations (2)

Experimental studies of supersonic film cooling with shock wave interaction

31st Joint Propulsion Conference and Exhibit (1995)

Takeshi Kanda Fumiei Ono Masahiro Takahashi Toshihito Saito Yoshio Wakamatsu

Electric shock

10.2514/6.1995-3141

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Citations (2)

Mach 6 Testing of a Scramjet Engine Model

Takeshi Kanda Toshihito Saito Kenji Kudo Tomoyuki Komuro Fumiei Ono

Scramjet

Source

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Citations (2)

Numerical Analysis of Scramjet Internal Flow by Hybrid Unstructured Grid Method.

JSME International Journal Series B (2000)

Masatoshi Kodera Yasutaka IGARASHI Kazuhiro Nakahashi Takeshi Kanda Tetsuo Hiraiwa

Computations of internal viscous flowfields of scramjet models were conducted at inflow Mach numbers of 3.4 and 5.45. A hybrid unstructured grid method was used to compute the scramjet models with and without a short strut. The numerical method to solve the Navier-Stokes equations on the hybrid unstructured grid was developed using a finite volume cell vertex scheme and the lower-upper symmetric Gauss-Seidel (LU-SGS) implicit time integration algorithm. The computational results revealed that a thick subsonic region did not exist in the combustor near the top wall at Mach number 5.45. It was a desirable feature to avoid unstarting the engine. With the use of a strut, the relatively low velocity regions increased and the downward flow toward the cowl behind the step became strong. An overconcentration of fuel toward the top wall during weak combustion was observed in the experiment. The reason for this was that the airflow near the injector was turned to the top wall due to the small influence of combustion in the experiment.

Scramjet

Inflow

Unstructured grid

10.1299/jsmeb.43.407

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Citations (1)

Numerical simulation of steady/unsteady Mach reflection using shock capturing schemes

cfd (1992)

Masahiro Takahashi Katsuhiro Ito Takeshi Kanda Koichiro Tani

Mach reflection

Reflection

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Citations (2)