• Journal of the Korean Society of Propulsion Engineers
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• v.19 no.6
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• pp.81-90
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• 2015

In order to know the characteristics of the hypersonic air-breahting engine, high altitude and Mach number ground test is necessary. Therefore, high pressure and high temperature condition should be simulated to do ground test of the hypersonic air-breathing engine. In this paper, the hypersonic air-breathing engine ground test facility of the Korea Aerospace Research Institute was introduced and the composition and characteristics were described.

• Journal of the KSME
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• v.32 no.9
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• pp.788-796
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• 1992

이 글에서는 극초음속 항공우주 비행기의 개요 및 개발배경, 구조기능 및 추진체계, 그리고 개발 및 설계의 제반고려사항 등에 관하여 알아보았다. 단단계형 공기흡입식 추진체계라는 새로운 개념의 도입은 미래 극초음속 비행체의 재활전용성과 항공 및 우주의 운항 용이성이라는 두 가 지의 가능성을 제시한다는 점에서 큰 의미를 갖고 있다. 극초음속 항공우주비행기의 실현가능 성은 공기흡입식 추진체계의 핵심부분인 스크램제트엔진 개발의 성공여부에 달려 있다고 하겠다. 이러한 스크램제트엔진에 관한 연구 및 개발은 현재 진행중이며, 오늘날 첨단 추진체 연구분야 중의 하나로 여겨지고 있다.

• Journal of the Korean Society of Propulsion Engineers
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• v.9 no.1
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• pp.67-83
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• 2005

The evolution of hypersonic scramjet engines was reviewed from the 1960s to the present. Concepts of hypersonic air-breathing propulsion systems based on scramjet engine, such as combined-cycle engine, were described and compared with other high-speed propulsion systems. The development history of scramjet engines over the past 40 years odd was introduced with priority given to the efforts in the United States, and the current status of scramjet technology was reviewed through the recent development programs in several developed countries.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.12
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• pp.1031-1038
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• 2017

In order to improve the performance of the air breathing engines, it is important to maximize the total pressure recovery through air intake. In this study, we investigated whether the Oswatitsch method, which guarantees the maximum pressure recovery for supersonic intake, is effective at hypersonic speed by compressing the intake air with the same intensity at each ramp. The non-linearity of the shock wave normal Mach number at each ramp stage was analyzed by comparing the compression ramp angle and the number of ramp to the inflow Mach number in terms of compressible thermodynamics and the operation limits of the inlet. Based on this analysis, the Oswaitisch technique yields valid conditions not only in supersonic but also hypersonic flight regime.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.326-330
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• 2011

Development and validation of performance analysis model for dual combustion ramjet engines has been performed. A typical performance model for hypersonic intake flow and supersonic mixing and combustion was demonstrated; Taylor-Maccoll equation for coaxial intakes and a quasi-one dimensional reacting flow analysis with CEA chemical equilibrium for supersonic combustion. The results, thermodynamic data of intake and supersonic combustor were validated with CFD numerical results.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.50 no.5
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• pp.297-308
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• 2022

Most air-breathing aircraft operated in the hypersonic region are equipped with a scramjet engine. In a scramjet engine, a shock wave generated at an inlet acts as a compressor for a general gas turbine engine instead, so total pressure loss caused by the shock wave is considered very important. In this study, to minimize total pressure loss, a method of designing an external compression inlet using isentropic compression surface was proposed, and an external compression inlet with 3-deflection angles and Busemann inlet were designed under the same conditions. After that, through computational analysis, the performance characteristics at off-design conditions were compared. Each inlet shape was truncated according to the length of the 3-ramp external compression inlet, and the boundary layer correction was performed. The isentropic external compression inlet showed superior performance at the design point, but under the off-design conditions, its performance was degraded compared to the 3-ramp external compression inlet.

• Journal of the Korean Society of Propulsion Engineers
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• v.14 no.3
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• pp.69-78
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• 2010

Korea Aerospace Research Institute started on design and development of a hypersonic air-breathing engine test facility from 2000 and completed the test facility installation in July 2009. This facility, designated as Scramjet engine test facility(SeTF), is a blow-down type high enthalpy wind tunnel which has a pressurized air supply system, air heater system, free-jet test chamber, fuel supply system, facility control/measurement system and exhaust system. In this paper, details of the specifications, and configuration of the SeTF are described. For verifying characteristics of the SeTF, wind tunnel tests are now on progress and some of the data are also described.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2002.04a
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• pp.61-61
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• 2002

스크램 제트 엔진의 설계에서 초음속으로 유입된 공기의 짧은 잔류시간으로 인한 연료-공기의 혼합은 가장 중요하며 해결하기 힘든 문제이다. 전헝적인 비행 조건에서 흡입 공기가 극초음속 비행기 엔진 내에서 잔류하는 시간의 단위는 1 ms 정도이어서 짧은 시간 동안 연료와 공기는 효율적으로 혼합되어야 하며, 최대의 추진력을 얻기 위하여 과도한 공력저항없이 연소 가능한 연료-공기 혼합기를 생성시킬 수 있는 효율적인 연료-공기의 혼합 방법이 요구된다. 현재까지 가장 많이 연구되어 온 혼합 방법은 엔진 입구로 들어오는 공기 유동에 수직 방향으로 연료를 분사하는 것으로 이 방법은 연료 유동 방향과 공기 유동 방향이 수직이기 때문에 추력 손실이 생기는 단점을 갖고 있지만, 초음속으로 유입되는 공기에 수직으로 연료를 분사하게되면 분사 위치 앞에 궁형 충격파가 생겨서 감속되어 유동이 회전하는 재순환영역이 생기고 연료의 혼합이 잘 이루어지는 장점이 있다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.289-292
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• 2007

Performance of a dual mode ramjet engine based on the sensitivity analysis of design parameters (the gap between cowl and inlet spike and combustor length) was analyzed from the view points of aerodynamics and thermodynamics. A dual mode engine performing from supersonic to hypersonic (Mach no. 2 to 6) was designed in a proposed flight envelop. The design method and result were comparable to the results of the previous study, Hyperion RLV, and the CFD calculation.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.394-398
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• 2005

Ramjet engine have been usually operated on Mach $1.5\sim3$ as the vehicle of supersonic cruising engine and studied about the higher performance above Mach 4. The research of Duel mode Scramjet engine which have duel operating mode of ramjet/Scramjet are in progress actively nowadays. This paper suggests the effect the flow characteristics and the effects of back pressure, angle of attack, angle of yow on the supersonic air intake on mach 4 through the Schlieren/Oil flow visualization, and pressure measurement on experimental model.