• 한국소음진동공학회논문집
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• 제24권3호
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• pp.171-179
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• 2014

썬루프 버페팅 현상은 차량 주행시 발생하는 주요 바람소리 문제점 중 하나이다. 버페팅 문제점을 해결하기 위해서 전산 해석을 적용한다면, 실험적 방법보다 비용을 절감할 뿐 아니라 발생 원리 또한 규명할 수 있다. 그러나 전산 해석을 이용하기 위해서는 해석 결과의 정확성이 보장되어야 실제 차량 개발에 적용할 수 있다. 이 연구에서는 해석적 방법의 정확도 향상을 위해 주요 상업용 전산해석 소프트웨어들의 썬루프 버페팅 현상 예측에 대한 벤치마크 테스트를 수행하였다. 해석 대상은 차량의 형상을 간략하게 만든 HSM(Hyundai simplified model)을 이용하였고, 정확도 비교를 위해 속도별 버페팅 현상에 대한 실험을 현대자동차 공력무향풍동에서 실차내부의 흡음재에 의한 효과를 해석적으로 고려하기 위해 음향 응답 실험을 수행하여 해석 결과 정확도 향상을 위해 각 상용 소프트웨어 제작사에 해석 전에 제공 하였다. 이 연구를 통해 대부분의 상용 소프트웨어들이 실험결과와 유사한 해석 결과를 도출하였다. 또한, 실제 차량 개발에서 적용하기 위한 해석 예측 우선순위를 서로 공유하여 추가 해석을 통해 차량 개발에 적용 가능한 보다 정밀한 해석 정확도를 얻어낼 수 있었다.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2001년도 추계학술대회논문집B
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• pp.746-751
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• 2001

We used a cylindrical model which simulates turbine blade leading edge to investigate the effects of free-stream turbulence intensity and blowing ratio on film cooling of turbine blade leading edge. Tests are carried out in a low-speed wind tunnel on a cylindrical model with three rows of injection holes. Mainstream Reynolds number based on the cylinder diameter was $7.1\times10^4$. Two types of turbulence grid are used to increase a free-stream turbulence intensity. The effect of coolant blowing ratio was studied for various blowing ratios. For each blowing ratios, wall temperatures around the surface of the test model are measured by thermocouples installed inside the model. Results show that blowing ratios have small effect on spanwise-averaged film effectiveness at high free-stream turbulence intensity. However, an increase in free-stream turbulence intensity enhances significantly spanwise-averaged film effectiveness at low blowing ratio.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2007년도 춘계학술대회A
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• pp.1120-1125
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• 2007

Experimental study on the control of randomly disturbing system is conducted. External and internal disturbances are imposed to the system in combined manner. A vertical propeller system exposed horizontal weak turbulent air flow is chosen as an experimental model. The aim of the control system is to maintain the angular position of vertical propeller in parallel to air flow. Trajectory Tracking Stochastic Controller (TTSC) is designed to ensure system's stability while following system command. The Trajectory Tracking Stochastic Controller is composed of two controller, one is stochastic controller to suppress internal random noise and the other one is trajectory-tracking controller to follow the command having random noise. The proposed hybrid controller, TTSC, shows remarkable performance in pitch control of vertical propeller system in wind-tunnel test

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2008년도 학술대회
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• pp.245-250
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• 2008

For simulation of a wing unfolding motion for the various aerodynamic conditions, equation governing unfolding motion and moments applying to the unfolding wing were modelled. Aerodynamic roll moment consists of the static roll moment and the damping moment, which were obtained through wind tunnel tests and numerical analyses respectively. Panel method was used to compute the roll damping coefficient with twisted wing, whose deflection angle was equivalent to angle of attack due to the deployment motion. Roll damping coefficient is a function of angle of attack, sideslip angle, and deployment angle but not of angular velocity of deployment. Simulation with aerodynamic damping model gave more similar deployment time compared to wing deployment test results.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2008년 추계학술대회논문집
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• pp.245-250
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• 2008

For simulation of a wing unfolding motion for the various aerodynamic conditions, equation governing unfolding motion and moments applying to the unfolding wing were modelled. Aerodynamic roll moment consists of the static roll moment and the damping moment, which were obtained through wind tunnel tests and numerical analyses respectively. Panel method was used to compute the roll damping coefficient with twisted wing, whose deflection angle was equivalent to angle of attack due to the deployment motion. Roll damping coefficient is a function of angle of attack, sideslip angle, and deployment angle but not of angular velocity of deployment. Simulation with aerodynamic damping model gave more similar deployment time compared to wing deployment test results.

• International Journal of Aeronautical and Space Sciences
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• 제6권2호
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• pp.33-45
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• 2005

The 1/9-scale model of a fighter-type configuration was tested in the Micro-Craft 8ft ${\times}$ 12ft wind tunnel facility. An abrupt lift dump was found at a certain range of angle of attack under the pre-scheduled approach configuration. To avoid a probable unsatisfactory flight behavior due to the lift dump, various aerodynamic devices were suggested. Extensive tests applying the cutoff leading edge flaps, boundary layer fences, saw tooth and vortex generators were performed with flow visualization as well as force and moment measurements. Test results showed that the origin of the lift dump was caused by the secondary boundary layer flow separation generated from the strong interaction between wing and flap. Various solutions for avoiding the unfavorable feature were suggested with the merits and demerits.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2002년도 춘계 학술대회논문집
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• pp.53-58
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• 2002

A three-dimensional incompressible Navier-Stokes solver is developed for the flow analysis around Micro Air Vehicle(MAV) designed by MACDL(Micro Aerodynamic Control and Design Lab), Seoul National Univ., Validations of this solver are presented for two cases, first flow over the circular cylinder with infinite length, second flow over infinite wing with wing section, E387 airfoil. Simultaneously, Wind Tunnel test is performed with Flatform Wire type sir-component balance and model designed by MACDL. The numerical results are also examined through comparison with experimental data.

• International Journal of Aeronautical and Space Sciences
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• 제18권3호
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• pp.498-511
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• 2017

This work conducts a validation study for loads analysis of the UH-60A slowed rotor at high advance ratios. The nonlinear flexible multibody dynamics analysis code, DYMORE II, is used with a freewake model for the rotorcraft comprehensive analysis. Wind tunnel test data of airloads and structural loads of a full-scale UH-60A slowed rotor are used for this validation study. This analysis predicts well the thrust reversal phenomenon at the advance ratio of 1.0. The section airloads such as normal forces and pitching moments and the oscillatory blade structural moments in this analysis are compared well or moderately with the measured data, although the higher harmonics components of blade torsion moments are not captured well. This validation study assesses the prediction accuracy and investigates the unique aeromechanics characteristics of a slowed rotor at high advance ratio.

• 대한토목학회논문집
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• 제26권6A호
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• pp.1013-1022
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• 2006

본질적으로 두 개의 I형 거더를 가진 사장교는 공기역학적으로 불리한 특성을 가지고 있음에도 불구하고 경제적으로 유리하기 때문에 최근 우리나라에서 많이 건설되고 있다. 본 논문에서는 두 개의 I형 거더를 가지는 사장교의 실제 조건 하에서의 공기역학적 특성을 평가하기 위하여 영각, 난류강도, 감쇠비를 변화시켜가면서 단면모형실험을 수행하였다. 비틀림 강성이 다른 두 개의 상부 단면 형식이 시공단계 및 완공 후에 대하여 각각 조사되었고 교량의 공기역학적 특성을 향상시키기 위하여 3가지 형식의 페어링이 고려되었다. 연구결과, 전통적인 등류에서의 단면모형실험은 다소 비관적으로 공기역학적 거동을 평가하고 있으며 교량의 바람에 의한 응답은 난류강도와 구조감쇠비에 따라 현저하게 변화하는 것을 확인하였다. 본 연구에서 제시된 페어링은 와류진동 및 버페팅 진동을 감소시켰으며 또한, 플러터의 발생속도도 증가시켰다. 본 연구결과는 두 개의 I형 거더를 가지는 사장교의 내풍설계를 위한 많은 정보를 제공할 수 있을 것으로 기대된다.

• International Journal of Aeronautical and Space Sciences
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• 제18권1호
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• pp.165-173
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• 2017

The aeromechanics predictions of HART I rotor obtained using a computational structural dynamics (CSD) code are evaluated against the wind tunnel test data. The flight regimes include low speed descending flight at an advance ratio of ${\mu}=0.151$ and cruise condition at ${\mu}=0.229$. A lifting-line based unsteady airfoil theory with C81 table look-up is used to calculate the aerodynamic loads acting on the blade. Either rolled-up free wake or multiple-trailer wake with consolidation (MTC) model is employed for the free vortex wake representation. The measured blade properties accomplished recently are used to analyze the rotor for the up-to-date computations. The comparison results on airloads and structural loads of the rotor show good agreements for descent flight and fair for cruise flight condition. It is observed that MTC model generally improves the correlation against the measured data. The structural loads predictions for all measurement locations of HART I rotor are investigated. The dominant harmonic response of the structural loads is clearly captured with MTC model.