• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.10
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• pp.20-27
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• 2004

In this study, CFD analysis for 2D ellipse and 3D CRW UAV are performed. Furthermore, flow analysis around a hub connecting body and rotor is analyzed and a strategy to reduce the drag caused by the hub is sought. Also, the idea of fairing installation is confirmed by a wind tunnel test.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2006.11a
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• pp.65-68
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• 2006

Experiments were performed to investigate the effects of mud-flap width on the aeroacoustic noise generation inside high-speed trains. The open-circuit type wind tunnel was used. The measurement setup was custom-built to simulate intercoach spacing. From the measurements, the characteristics of the turbulent flow after the intercoach spacing and consequent generation of aeroacoustic noise inside the cabin was investigated. Especially the effects of mud flap length on the characteristics of the characteristics of the turbulent flow were identified. The mechanism of noise generation by analyzed interactions with structure vibration characteristics and generation characteristics of blocked pressure was investigated.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2007.05a
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• pp.469-472
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• 2007

Aeroacoustic sound induced from inter-couch spacing is an important contributor to interior noise generation for high speed trains. Especially the open space between mud-flap has significant impact from flow-structure interactions. To understand noise generation mechanism, experiments were performed using the wind tunnel. To find mud-flap parameters for minimal noise generations the various shape of the mud-flap was installed and its effects on the wall-pressure generation were investigated.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.14-17
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• 2011

Numerical simulation was carried out for the SNECMA modulatable thrust devices, with four different nozzle contraction angle $45^{\circ}$, $60^{\circ}$, $83^{\circ}$, and $90^{\circ}$, respectively. Results show that $83^{\circ}$ nozzle contraction is better in that it comes up with good thrust level with small aerodynamic load.

• Proceeding of EDISON Challenge
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• 2012.04a
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• pp.17-20
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• 2012

본 연구는 전산유체해석 프로그램인 EDISON_CFD를 이용하여 NACA63-425 에어포일과 이 에어포일을 기반으로 만든 뒷전 두께가 2% 4%인 NACA63-425G02, NACA63-425G04에 대하여 두께 변화에 따른 공력 특성 변화를 수치해석을 수행 하였다. 난류점성내의 압축성 조건에서 받음각에 따른 양력계수, 항력계수, 양항비 등을 비교하여 Flatback 에어포일의 장단점에 대하여 결과를 분석해 보았다.

• Aerospace Engineering and Technology
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• v.5 no.2
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• pp.27-36
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• 2006

This paper describes the performance test procedures and results of NRSB-1M and NRSB-2M Not only aerodynamic performance test but also sound measurement test were performed for the small-scaled blades in the ground Total thrusts and torques of the rotor were measured using rotating balance for aerodynamic performance test. Sound pressure levels were measured using microphone in 1.64D distance for sound measurement test. Non-dimensionalized test data are compared and analyzed. Consequently, It was confirmed that NRSB-2 was better than NRSB-1.

• Aerospace Engineering and Technology
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• v.1 no.1
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• pp.128-134
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• 2002

Outer surfaces of KSR-III are insulated to protect outer structure and inner payloads from the aerodynamic heating. The characteristics of insulation material (BMS 10-102), selected through careful tests and thermal analyses, are low heat transfer rate and low density. It is applied in a wet and continuous spray pattern for outer surfaces of KSR-III. In the present study, the honeycomb sandwich structure of nose fairing, which is one of the typical multi-layer structures of KSR-III, is thermally analyzed with insulation.

• Proceeding of EDISON Challenge
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• 2016.03a
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• pp.610-613
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• 2016

항공기의 착륙 과정에서 지면효과에 의해 기체가 원하는 위치에 착지하지 못하는 경우가 있다. 이러한 현상들로 인해 항공기의 착륙 실패 또는 활주로 이탈로 인한 인명피해로 이어질 수 있다. 본 연구에서는 이러한 착륙과정에서 쓰이는 날개의 부품중 하나인 Spoiler에 대한 공력 해석을 EDISON 전산열유체 시스템을 이용하여 진행해 보았다. 특히 Spoiler의 전개 각도를 다양하게 변화시켜가며 그 전개 각도에 의한 Lift dumping effect에 초점을 맞추어 연구를 진행하였다. 예상과 동일하게 전개각도가 커질수록 양력은 감소하였으며 항력의 경우 선형적으로 증가하는 양상을 보였다. 또한 전개각도가 20도보다 커지는 구간부터는 양력이 음수로 작아지는 현상을 확인할 수 있었다.

• Proceeding of EDISON Challenge
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• 2016.11a
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• pp.96-100
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• 2016

슬롯판을 이용한 경사충격파와 경계층 간섭유동 제어에서, 슬롯의 각도를 바꾸어 가며 제어 성능을 비교하는 수치적 연구가 수행되었다. 기준이 되는 수직 슬롯, 각도를 달리한 6개의 case를 선정하여 하여 충격파 뒤에서 전압손실 및 경계층 안정성을 기준으로 제어 성능을 평가하였다. 수치해석 결과 모든 형상에 대해 제어하지 않은 상태보다 좋은 성능을 얻었다. 공력성능이 뛰어난 그룹과 그렇지 않은 그룹을 구분하여 슬롯과 공동 유동 구조를 분석하면서 경계층 불안정성을 야기하고 전압손실 감소에 영향을 미치는 것은 경계층과 충격파가 상호작용하는 영역에서 Vortex를 얼마나 제어할 수 있는지 여부임을 알 수 있었고, 이러한 Vortex를 얼마나 제어할 수 있는지에 따라 공력 성능이 결정됨을 파악할 수 있었다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.49 no.9
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• pp.721-727
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• 2021

In this paper, aerodynamic characteristics of missile configuration with various grid fins in subsonic flow. To investigate the effects of grid fin shape, four types of experimental models were used. In addition, to examine aerodynamic characteristics of missile configurations with various grid fins according to effects of Reynolds numbers and configurations of grid fins, 6-components aerodynamic forces and moments were measured by internal balance in wind tunnel test.