• Journal of the Korean Institute of Gas
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• v.14 no.2
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• pp.47-52
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• 2010

The development of energy saving system with pressure regulator has recently been received interests. Since the internal geometry in the pressure regulator is small and complex, the frictional loss in it is critical. In this study, the pressure loss with tip size, tip position, and mass flow was investigated using numerical approaches(CFD). The aimed reduction in pressure were achieved as the ratio of t/T was more than 0.8. In addition, there was no effect of the tip position.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.05a
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• pp.406-410
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• 2010

Current paper represents the air data acquisition and processing algorithm which can acquire the air data such as velocity and angle of attack by measuring the static pressure on the specific locations of a high speed aerial vehicle. Unlike the previous air data acquisition system, current system applied several pre-determined data obtained from computational fluid dynamic approach having enough sensor redundancy and fault detection ability. The verification of current algorithm was done by commercial software Matlab and Simulink.

• Proceedings of the Korean Geotechical Society Conference
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• 2006.03a
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• pp.131-136
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• 2006

일면전단시험은 전단면의 응력을 직접 측정하므로 평면변형시 강도를 파악할 수 있는 등의 많은 장점을 가지고 있으며, 시험조작이 간편하기 때문에 실용적으로도 우수한 것으로 판단된다. 그러나 사질토의 경우에 의한, Dilatancy에 의한 체적변화과정에서 공시체와 전단상자의 주면마찰력이 전단면의 수직 응력을 증감시키기 때문에 구해지는 강도가 과대 또는 과소하게 나타나는 것으로 알려져 있다. 그러나 반력판측에 장착한 하중계를 통해 전단면의 수직응력을 직접 측정 제어하는 형식으로 개선되어 주면마찰력의 영향을 해소하였다. 따라서 본 연구는 반력판측에 하중계를 장착한 개량형 다단식 단순전단시험기를 개발하여 사질토의 정압(CD)조건 전단시험을 수행하여 강도특성과 전단강도에 미치는 영향을 개량형 일면전단시험의 결과와 비교하였다. 그 결과 정압조건의 일면전단시험과 단순전단시험에 의한 강도정수는 조밀한 모래의 경우는 거의 비슷하게 나타나며, 느슨한 모래의 경우는 일면전단이 다소 크게 나타났다. 그리고 단순전단과 일면전단시험에서의 Dilatancy거동에는 큰 차이가 나타나지 않았다.

• Journal of the Korean Society of Propulsion Engineers
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• v.26 no.4
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• pp.10-20
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• 2022

The performance analysis test of the scramjet engine intake was conducted under the Mach 5 condition of the scramjet engine test facility, a free-jet ground test facility of the Korea Aerospace Research Institute. A pitot/static pressure rake installed at the rear of the isolator was designed and manufactured to measure the total pressure recovery rate and mass capture ratio, which are typical performance factors of the scramjet engine intake. The effect of the rake mounted at the rear of the isolator on the intake, the performance analysis measured by the rake, and the change in wall static pressure distribution according to the angle of attack were performed. Finally, the point at which the intake unstart occurred was confirmed by using the rear back pressure adjusting device, which simulates pressure rise in the combustor, and the results are summarized in this paper.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2000.04a
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• pp.15-15
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• 2000

제트 베인에 의한 추력 방향 제어 장치는 롤 운동 제어를 가능하게 하고, 큰 선회 각도를 얻을 수 있는 장점이 있으나, 기계 장치가 비교적 복잡하고, 제트 베인의 열적, 구조적 문제를 해결하여야 한다. 복잡한 기계 장치는 유동 해석의 측면에서 고려해 볼 때 격자 형성을 어렵게 만들어 유동장 해석을 통한 성능예측을 어렵게 만든다. 구조물의 응력해석을 위하여 제트 베인 표면에서의 정압력과 더불어 마찰력도 고려하여야 하는데, 정확한 마찰력 계산을 위해서는 난류 모델링이 필수적이고, 그에 따라 벽면 근처에서 격자를 밀접시키는 것이 요구된다. 본 연구에서는 상용 유동해석 소프트웨어인 Fluent를 사용하여 제트 베인이 장착된 추력 방향 제어 장치의 3차원 난류 유동장 계산을 수행하였다. 피치, 요 운동의 경우와 롤 운동의 경우로 구분하여 계산하였으며, 최대 받음각을 $25^{\cire}$ 로 하여 제트 베인의 받음각에 따라 회전축에 작용하는 힘과 모멘트를 계산하였다. 본 연구의 결과는 향후 개발될 제트 베인이 장착된 추력 방향 제어 장치의 개념설계 단계에 필요한 기본자료로서 신뢰도를 높이는데 도움이 되리라 판단된다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.359-363
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• 2011

In this paper, the characteristic of pressures had been analyzed with a series of shapes that are pressure probes used in supersonic wind tunnel. When a performance of supersonic wind tunnel is evaluated, the Mach number is calculated by using the ratio of static pressure in test section wall to total pressure in settling chamber. Also the flow condition can be visualized by schlieren system. However a number of limitations exist to measure pressure of test section due to high speed and boundary layer effect. Therefore a specific pressure probe is needed for evaluating flow condition in test section at a various of positions. In the paper, experiments were conducted in terms of some pitot probes and the results were compared and analyzed.

• Journal of the Korean Society of Propulsion Engineers
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• v.14 no.1
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• pp.48-55
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• 2010

The purpose of this paper was to address the methodology of the air flow measurement using duct mach number that was considered area-weighed average obtained by total, static pressure and temperature measured at engine inlet duct. Without installing boundary rake, the prediction of air flow measurement was discussed. Actual air flow measurement and pressure value using pressure loss through inlet seal were described to improve the reliability and operability of altitude engine test facility.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.38 no.12
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• pp.991-997
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• 2014

This study investigated the swirling flow fields of a gun-type gas burner (GTGB) without a combustion chamber under cold flow conditions. Three velocity components and the static pressure were measured with a straight-type five-hole pressure probe (GHPP) using a non-nulling calibration method and compared with the results of an X-type hot-wire probe (X-probe) and computational fluid dynamics (CFD). The GHPP measured the velocity and static pressure for the swirling flow of the central region of the GTGB better than the X-probe but produced slightly worse results than the CFD.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.2
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• pp.136-142
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• 2007

A small supersonic wind tunnel was designed and built to study the flow characteristics of a supersonic impulse turbine cascade. The supersonic cascade with a 2-dimensional supersonic nozzle was tested for the axial gap ratio (${\delta}$) of the supersonic turbine that is the one of the turbine design parameter. Firstly, the flow was visualized by a single pass Schlieren system. Next, total and static pressure of the cascade were measured by a pressure scanning system. Highly complicated flow patterns including shocks, nozzle-cascade interaction and shock boundary layer interactions, flow characteristics of the supersonic turbine were observed.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.05a
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• pp.361-366
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• 2006

A small supersonic wind tunnel was designed and built to study the flow characteristics of a supersonic impulse turbine cascade. The supersonic cascade with a 2-dimensional supersonic nozzle was tested for the leading edge chamfer angle $(\gamma)$ of the supersonic turbine that is the one of the turbine design parameter. Firstly, the flow was visualized by a single pass Schlieren system. Next, total and static pressure of the cascade were measured by a pressure scanning system. Finally, highly complicated flow patterns including shocks, nozzle-cascade interaction and shock boundary layer interactions, flow characteristics of the supersonic turbine were observed.