• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.613-617
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• 2011

Korea Aerospace Research Institute has been designed and manufactured various thurst nozzles of the scramjet engine for optimized configuration. The test campaign for thurst nozzle characteristics was performed at T4 free-piston shock tunnel in University of Queensland, Australia. Total 8 kinds of thrust nozzles and 2 kinds of side walls were manufactured for this campaign. In this paper, the design and specification of thrust nozzles was reported. Based on the static pressure distribution of the engine and pitot pressure distributions at nozzle exit, The positive net thurst was observed with baseline case of the test campaign.

• Journal of Ocean Engineering and Technology
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• v.27 no.1
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• pp.31-36
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• 2013

In this paper, the effects of a foil attached to a ship on the ship motion, added resistance, and thrust generation in waves are analyzed. The unsteady theory for a two-dimensional foil is introduced to determine the coupled motion responses of the ship and foil. The thrust caused by the oscillating foil is evaluated and compared to the added resistance of the ship, so that a positive net thrust can be possible in waves. A comparison of the results of unsteady, quasi-steady, and experimental analyses is performed.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.1-1
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• 2005

Japan Aerospace Exploration Agency(JAXA) has been conducting research and development of the Scramjet engines and their derivative combined cycle engines as hypersonic propulsion system for space access. Its history will be introduced first, and its recent advances, focusing on the engine performance progress, will follow. Finally, future plans for a flight test of scramjet and ground test of combined cycle engine will be introduced. Two types of test facilities for testing those hypersonic engines. namely, the 'Ramjet Engine Test Facility (RJTF)' and the 'High Enthalpy Shock Tunnel (HIEST)' were designed and fabricated during 1988 through 1996. These facilities can test engines under simulated flight Mach numbers up to 8 for the former, whereas beyond 8 for the latter, respectively. Several types of hydrogen-fueled scramjet engines have been designed, fabricated and tested under flight conditions of Mach 4, 6 and 8 in the RJTF since 1996. Initial test results showed that the thrust was insufficient because of occurrence of flow separation caused by combustion in the engines. These difficulty was later eliminated by boundary-layer bleeding and staged fuel injection. Their results were compared with theory to quantify achieved engine performances. The performances with regards to combustion, net thrust are discussed. We have reached the stage where positive net thrust can be attained for all the test coditions. Results of these engine tests will be discussed. We are also intensively attempting the improvement of thrust performance at high speed condition of Mach 8 to 15 in High Enthalpy Shock Tunnel (HIEST). Critical issues for this purposemay be air/fuel mixing enhancement, and temperature control of combustion gas to avoid thermal dissociation. To overcome these issues we developed the Hypermixier engine which applies stream-wise vortices for mixing enhancement, and the M12-engines which optimizes combustor entrance temperature. Moreover, we are going to conduct the flight experiment of the Hypermixer engine by utilizing flight test infrastructure (HyShot) provided by the University of Queensland in fall of 2005 for comparison with the HIEST result. The plan of the flight experiment is also presented.

• 한국연소학회:학술대회논문집
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• 2012.11a
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• pp.297-299
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• 2012

Korea Aerospace Research Institute has been doing researches on the hypersonic propulsion system and hypersonic wind-tunnel since 2000 and started scramjet engine researches from 2005. Total 5 kinds of scramjet engine were designed and tested and two of them were hydrocarbon-fueled scramjet engine. For verifying the own characteristics of each components like the intake and combustor, several component tests were done at the KSPC of JAXA and KARI. In this paper, current scramjet engine research activities of KARI will be described.