• 한국항공우주학회지
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• 제49권2호
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• pp.85-93
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• 2021

본 논문에서는 반경험적 해석도구를 이용하여 일반적인 형상의 꼬리날개 조종 유도무기의 공력 특성을 예측하고 그 결과를 보정하는 연구를 수행하였다. 반경험적 해석도구의 공력 특성 예측 결과를 풍동시험 결과와 비교하여 오차 원인을 확인하였으며, 반경험적 해석도구의 주요 오차 요인은 주날개-꼬리날개 간 간섭 성분임을 확인하였다. 반경험적 해석 결과를 풍동시험 결과와 전산해석 결과를 이용하여 보정하였으며, 보정된 데이터가 풍동시험 결과와 잘 일치함을 확인하였다. 본 연구를 통해 일반적인 꼬리날개 조종 유도무기의 공력 특성을 반경험적 해석도구를 이용하여 예측할 때 날개 간 간섭 성분 보정이 필요함을 확인하였다.

• Structural Engineering and Mechanics
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• 제56권6호
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• pp.1021-1040
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• 2015

An effective method to calculate aerodynamic loads and aeroelastic responses of large wind turbine tower-blade coupled structures in yaw condition is proposed. By a case study on a 5 MW large wind turbine, the finite element model of the wind turbine tower-blade coupled structure is established to obtain the modal information. The harmonic superposition method and modified blade-element momentum theory are used to calculate aerodynamic loads in yaw condition, in which the wind shear, tower shadow, tower-blade modal and aerodynamic interactions, and rotational effects are fully taken into account. The mode superposition method is used to calculate kinetic equation of wind turbine tower-blade coupled structure in time domain. The induced velocity and dynamic loads are updated through iterative loop, and the aeroelastic responses of large wind turbine tower-blade coupled system are then obtained. For completeness, the yaw effect and aeroelastic effect on aerodynamic loads and wind-induced responses are discussed in detail based on the calculating results.

• 항공우주기술
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• 제9권1호
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• pp.35-41
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• 2010

고속으로 비행하는 물체는 공력가열에 의해 온도가 상승한다. KSLV-I 비행 중 공력가열 조건을 예측하는 방법으로 MINIVER를 이용하는 방법과 전산유동해석(CFD)기법을 이용하는 방법이 있다. MINIVER는 경험적 기법을 이용하여 대류열전달계수 및 회복온도를 산출하며, CFD 기법은 실제 유동장을 해석하여 발사체 표면에서의 공력가열조건을 산출한다. 본 연구에서는 CFD 기법을 이용하여 얻은 공력가열조건을 PLF 구조물 외부 표면에 적용하여 PLF 내부 온도장을 해석하고 그 결과를 KSLV-I 1차 비행시험 결과와 비교하였다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년 영문 학술대회
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• pp.6-15
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• 2008

This paper deals with the aeroelastic instability of vibrating multiple blade rows under aerodynamic coupling with each other. A model composed of three blade rows, e.g., rotor-stator-rotor, where blades of the two rotor cascades are simultaneously vibrating, is considered. The displacement of a blade vibrating under aerodynamic force is expanded in a modal series with the natural mode shape functions, and the modal amplitudes are treated as the generalized coordinates. The generalized mass matrix and the generalized stiffness matrix are formulated on the basis of the finite element concept. The generalized aerodynamic force on a vibrating blade consists of the component induced by the motion of the blade itself and those induced not only by vibrations of other blades of the same cascade but also vibrations of blades in another cascade. To evaluate the aerodynamic forces, the unsteady lifting surface theory for the model of three blade rows is applied. The so-called k method is applied to determine the critical flutter conditions. A numerical study has been conducted. The flutter boundaries are compared with those for a single blade row. It is shown that the effect of the aerodynamic blade row coupling substantially modifies the critical flutter conditions.

• 한국전산유체공학회지
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• 제13권2호
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• pp.1-7
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• 2008

For Aerodynamic analysis of vehicle at altitude, 100km, the validity of governing equations based on continuum model, was reviewed. Also, as the preliminary study for the sub-orbital space plane development, a candidate geometry was suggested and computational fluid dynamic(CFD) analysis was performed for various angles of attack in subsonic and supersonic flow regimes to analyze the aerodynamic characteristics and performance. The inviscid flow analyses showed that the stall starts at angle of attack above $20^{\circ}$, the maximum drag is generated at angle of attack, $87^{\circ}$ and the maximum lift to drag ratio is about 8 in subsonic flow. In supersonic, the stall angle is about $40^{\circ}$ and the maximum drag is generated at angle of attack, $90^{\circ}$. Also, mach number distribution of re-entry vehicle was computed versus altitudes.

• 한국소음진동공학회논문집
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• 제22권3호
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• pp.244-252
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• 2012

Recently, the speed of a train has been increased. So the trains are being exposed to wind more severely than before. Because of the operation of high speed trains and lightweight of the train, risks of train derailment have being increased. In this study, aerodynamic effects of a newly designed high speed train, HEMU-400x, are evaluated. For aerodynamic effect evaluation, analysis method is selected by examining the safety standards for high speed train. The condition of aerodynamic effects is selected by adverse effect conditions. In order to calculate $C_s$ coefficients, numerical analysis is conducted. Using $C_s$ coefficients, the side force is calculated. Through dynamics analysis, derailment and wheel unloading are obtained. Using these results, derailment evaluation is performed.

• 한국전산유체공학회지
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• 제17권2호
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• pp.28-34
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• 2012

In this study, the reliability-based design optimization of the airfoil was performed. PARSEC function was used to consider the uncertainty of the aerodynamic shape for the reliability-based shape optimization of airfoils. Among various reliability analysis methods, the moment method was used to compute the probability of failure of the aerodynamic performance. The accuracy of the reliability analysis was compared with other methods and it was found that the moment method predicts the probability of failure accurately. Deterministic and reliability-based optimizations were performed for the shape of the airfoil and it was demonstrated that reliability-based optimum assures the aerodynamic performances under uncertainties of the shape of the airfoil.

• Structural Monitoring and Maintenance
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• 제4권2호
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• pp.175-194
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• 2017

Research to date has mainly focused on structural analysis and design of wind turbines considering turbulent aerodynamic loading. The combined effects of wind and seismic loading have not been studied by many researchers. With the recent expansion of wind turbines into seismically active regions research is now needed into the implications of seismic loading coupled with turbulent aerodynamic loading. This paper proposes a monitoring procedure for onshore horizontal axis wind turbines (HAWTs) subjected to this combined loading regime. The paper examines the impact of seismic loading on the 5-MW baseline HAWT developed by the National Renewable Energy Laboratory (NREL). A modified version of FAST, an open-source program developed by NREL, is used to perform the dynamic analysis.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1996년도 한국자동제어학술회의논문집(국내학술편); 포항공과대학교, 포항; 24-26 Oct. 1996
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• pp.1308-1311
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• 1996

We propose a new linearized model which can be used very efficiently for the design and analysis of the autopilot of aerodynamically controlled skid-to-turn missiles. Proposed model is based on the linearized equations of the missile dynamics derived in the aerodynamic frame where xz plane contains the missile longitudinal axis and velocity vector. However, to take the effect due to the small perturbation of the missile body into consideration, we introduce a new frame which is identical to the aerodynamic frame in the trim state but after small perturbation it moves fixed with the missile body, and finally, the proposed model is set up in this frame. It is shown by nonlinear simulations and stability analysis of a numerical example that the new model describes the missile motion better than the conventional one linearized in the body frame with a certain amount of simplification.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2007년도 추계 학술대회논문집
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• pp.100-110
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• 2007

A new design approach for a delicate treatment of complex geometries such as a wing/body configuration is arranged using overset mesh technique under large scale computing environment for turbulent viscous flow. Various pre- and post-processing techniques which are required of overset flow analysis and sensitivity analysis codes are discussed for design optimization problems based on gradient based optimization method (GBOM). The overset flow analysis code is validated by comparing with the experimental data of a wing/body configuration (DLR-F4) from the 1st Drag Prediction Workshop (DPW-I). In order to examine the applicability of the present design tools, careful design works for the drag minimization problem of a wing/body configuration are carried out by using the developed aerodynamic shape optimization tools for the viscous flow over multiple-body aircraft geometries.