• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.48 no.1
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• pp.23-33
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• 2020

In this study, the effect of surface roughness distribution and its influence on the inflight icing code was investigated. Previous numerical studies focused on the magnitude of surface roughness, and the effects were only addressed in terms of changes in thermal boundary layers with fully turbulent assumption. In addition, the empirical formula was used to take account the turbulent transition due to surface roughness, which was regarded as reducing the accuracy of ice shape prediction. Therefore, in this study, the turbulent transition model based on the two-equation turbulence model was applied to consider the effects of surface roughness. In order to consider the effect of surface roughness, the transport equation for roughness amplification parameter was applied, and the surface roughness distribution model was implemented to consider the physical properties. For validation, the surface roughness, convective heat transfer coefficient, and ice shape were compared with experimental results and other numerical methodology. As a result, it was confirmed that the excessive prediction of the heat transfer coefficient at the leading edge and the ice horn shape at the bottom of the airfoil were improved accordingly.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.18 no.1
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• pp.89-99
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• 2010

The purpose of this study is analysis of Korean peninsula aircraft turbulence using the numerical weather prediction model, KWRF with the various turbulence index and pilot weather report data. Compared with the pilot weather report data and Calculated the turbulence index using the KWRF model result, many turbulence index show the similar horizontal distribution, except for the TUB2 and VWS. The analysis of vertical structure of turbulence, there are some difference each turbulence index respectively, but severe turbulence turn up in 15,000ft almost turbulence index. above 20,000ft height, intensity of turbulence vary each turbulence index. Through this turbulence study, It is founded on the research and development of the Korean peninsula aircraft turbulence

• 한국항공운항학회:학술대회논문집
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• 2015.11a
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• pp.102-106
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• 2015

항공 운송량의 증가로 운항 중 예상치 못한 난류(Turbulence)에 직면하는 경우도 증가하고 있다. 이로 인한, 손님/승무원의 부상, 화물 손상, 항공기 효율성 하락 등으로 많은 Cost가 발생하고 있으며, 항공 안전에도 치명적인 위협이 되고 있다. 하지만, 이에 대한 정보는 운항 중인 항공기의 조종사기상보고(Pilot Weather Reports, PIREP)에 의존하여 발생 지역을 예측하고 있으나, 보고시간 지체에 따른 부정확한 위치, 주관적인 강도 예측으로 실제 유사 지역을 운항하는 항공기에 도움을 주는데 한계가 있다. 금번 논문에서 TAPS(Turbulence Auto PIREP System)의 원리와 실제 운영하는 항공사의 활용 방안을 고찰하여, 정보의 자동 송/수신을 통한 실시간 난류 정보 제공으로 위험 요인을 사전 인지하여 제거할 수 있는 방안을 살펴보고자 한다.

• Journal of Institute of Convergence Technology
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• v.12 no.1
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• pp.25-30
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• 2022

도심항공교통은 다수의 전기추진 수직이착륙 항공기가 이착륙 가능한 버티포트가 필요하다. 빌딩풍은 고층건물 주변부에서 발생하는 강풍으로 항공기 이착륙과정에서 항공기의 비행 안전성을 크게 훼손시킬수 있다. 본 연구에서는 항공기 이착륙시 발생할 비행안정성 분석을 위하여 먼저 빌딩풍 주변의 유동특성을 분석하는 연구를 수행하였다. 유동해석은 상용CFD 소프트웨어인 SimericsMP를 사용하였으며, 난류 모델은 k-ε RNG 모델을 사용하였다. 해석방법의 타당성을 검증하기 위하여 CAARC 빌딩모델의 표면 압력 계산결과를 풍동시험 결과와 비교⋅검증하였다. 두 개의 고충빌딩이 있는 상황을 가정한 후, 빌딩풍이 빌딩 주변부의 속도분포 변화에 미치는 영향을 분석하였다. 두 개의 고층 건물 사이의 거리가 증가하는 경우 와들 사이의 상호작용이 감소하는 것을 확인했다. 향후 본 연구를 확장하여 다양한 형상의 고충건물이 밀집해 있는 도심지역에 대한 유동해석 연구를 진행하고자 한다.

• 한국항공운항학회:학술대회논문집
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• 2007.12a
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• pp.18-20
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• 2007

• Journal of the Korean Society for Aviation and Aeronautics
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• v.15 no.4
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• pp.94-99
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• 2007

The purpose of this study is analysis of aircraft turbulence of mid Korea using VWS from Osan radiosonde data and comparison with the PIREPs reporting the aircraft turbulence during $1990{\sim}1999$. The results of this study summarized that the frequence of aircraft events is more higher in winter time and in lower level(near the surface) of the atmosphere from VWS analysis using radiosonde data. And comparison with PIREPs data shows that relatively high skill score(44%) using the VWS method. It appears that the operational forecast skill score of aircraft turbulence is much higher using VWS than empirical method, due to the upgrade of the discrimination criteria of the aircraft turbulence.

• 한국전산유체공학회:학술대회논문집
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• 2011.05a
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• pp.420-427
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• 2011

In this study, numerical simulations of transonic aircraft configurations are performed with various turbulence models and the effect of turbulence models on flow separation are examined. A three-dimensional RANS code and three turbulence models are used for the study. The turbulence models incorporated to the code include Menter's ${\kappa}-{\omega}$ model, Coakley's $q-{\omega}$, and Huang and Coakley's ${\kappa}-{\omega}$, model. Using the code, numerical simulations of DLR-F6 configurations obtained from AIAA CFD Drag Prediction Workshop are conducted. Flow separations on the wing-body juncture and the wing lower surface near pylon are observed. and flow features of the regions are compared with experimental data and other numerical results.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.19 no.3
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• pp.54-60
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• 2011

The purpose of this study is verification of threshold of the aircraft turbulence index and icing index using PIREPs and KWRF on Korean peninsula, to operational weather support. There is improvement in new threshold value made of the pilot weather report data and the turbulence and icing index from KWRF model result, using the ROC Diagram method. the accuracy is up to 0.6 compared with the precedent study result 0.5. Through this study, It is founded on the research and development of the Korean peninsula aircraft turbulence and icing.

• Journal of Energy Engineering
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• v.12 no.1
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• pp.11-16
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• 2003

A numerical study was performed on the transient fuel temperatures of a military aircraft stationed under non-operating static condition. Numerical calculation was peformed by an explicit method using modified Dufort-Frankel scheme. It was assumed that the non-operating aircraft is subjected to repeated daily cycles of air temperature with the solar radiation and wind speed corresponding to the 1 % hot day ambient condition. And, the aircraft was assumed to be in turbulent flow. The convective heat transfer coefficient for turbulent flow on the flat plate suggested by Eckert was employed to calculate heat transfer between the aircraft surface and the ambience. The energy conservation equation on fuel was used as governing equation for this analysis. As a result of this analysis, the wing tank temperature showed the highest temperature and the largest rate of temperature changes among fuel tanks. The results of this analysis could be used as initial foe] temperatures for analysis of the transient fuel temperatures in various flight missions. Also, this analysis method could be used to analysis and design of an aircraft thermal energy management system.

• Journal of the KSME
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• v.34 no.9
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• pp.705-710
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• 1994

열.유체유동 중 난류에 대한 유동현상은 매우 광범위한 영역에서 나타나기 때문에 그 응용성이 매우 크게 작용되어 상업용 설비, 항공기, 자동차, 연소기 및 각종 스포츠 등에 이르기까지 넓게 적용되고 있다. 본 계측법은 특히 기하학적 형상에 좌우되지 않는 범용데이터 처리와 결부시켜 이용하는 것으로 최근 컴퓨터의 보급이 활발히 정착됨에 따라 보다 정확한 방법으로 난류의 정량적인 자료와 정성적인 난류구조를 계측하기 위하여 컴퓨터와 온라인으로 연결한 열선한 열 선유속계의출력을 통계해석에 의해 분석하는 방법이 시도되고 있는 것이다. 끝으로 이 글에서 언급한 삼축 열선 프로브는 프로브의 제작에 대한 고도의 기술과 프로브의 겁사체적을 되도록 작게 해야 하는 과제를 안고 있으며, 이러한 문제들은 제작기술의 발달로 점차 해결되고 있으며 적용대상이 크기 때문에 앞으로 많이 이용 될 것으로 기대되는 바이다.