• 한국군사과학기술학회지
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• 제12권5호
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• pp.683-688
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• 2009

A research was conducted about the Reynolds number effect on the projectile with an altitude change. The atmosphere conditions change in accordance with an altitude change. It effects the Reynolds number. To confirm how the phenomena affect the trajectory of the projectile, a computer program is designed with an altitude and a range considered. The MISSILE DATCOM which is based on the semi-empirical method was utilized to get aerodynamic coefficients. The result shows that the Reynolds number considerably changes as the altitude change. It causes to change the drag coefficient of the projectile. As the Reynolds number decreases, the skin friction drag increases significantly. It causes to decrease the maximum altitude and the range.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2000년도 춘계학술대회논문집B
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• pp.541-547
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• 2000

Experiments were done for the comparison of performance and flow characteristics between a two stage axial flow fan and a counter-rotating axial flow fm. The fan performance curves were obtained by the Korean Standard Testing Methods for Turbo Fans and Blowers (KS B 6311). The fan flow characteristics were measured using a five-hole probe by the non-nulling method. Each stage of the two stage axial flow fan used for the present study has an eight bladed rotor and thirteen stator blades. The front and the rear rotor of the counter-rotating axial flow fan have eight blades each and are driven by coaxial counter rotating shafts through a gear box located between the rear rotor and the electric motor. Both of the two axial fan configurations use identical rotor blades and the same operating conditions for the one-to-one comparison of the two. Performance characteristics of the two configurations were obtained and compared by varying the blade setting angles and axial gaps between the blade rows. The passage flow fields between the hub and tip of the fans were measured and analyzed for the particular operating conditions of peak efficiency, minimum and maximum pressure coefficients.

• 한국가시화정보학회지
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• 제13권1호
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• pp.9-14
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• 2015

There have been many attempts to reduce the cost of transportation. Especially, drag reduction of heavy vehicles has enormous influence on energy saving by reducing the driving power of the vehicles. In this study, the effects of drag-reducing additive devices such as side skirt, boat tail and cab-roof fairing on the drag reduction of a 5 ton truck model were experimentally investigated. The aerodynamic performance of these flow-control devices attached to heavy vehicle was evaluated through wind tunnel test. In addition, flow patterns around the truck model were visualized by using smoke tube method. The drag coefficient is reduced by up to 5.7%, 7.16% and 22.2% by the side skirt, boat tail and cab-roof fairing, respectively. The interactive effect of the side skirt and boat tail was also investigated.

• Advances in aircraft and spacecraft science
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• 제2권3호
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• pp.329-343
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• 2015

This study aimed to observe the effect of a novel concept (referred to as the flap extension) implemented on the leading edge of the flap of a three element high lift device. The high lift device, consisting of a flap, main element and slat is designed around an Airbus research profile for sufficient take off and landing performance of a large commercial aircraft. The concept is realised on the profile and numerically optimised to achieve an optimum geometry. Two different optimisation approaches based on Genetic Algorithm optimisations are used: a zero order approach which makes simplifying assumptions to achieve an optimised solution: as well as a direct approach which employs an optimisation in ANSYS DesignXplorer using RANS calculations. Both methods converge to different optimised solutions due to simplifying assumptions. The solution to the zero order optimisation showed a decreased stall angle and decreased maximum lift coefficient against angle of attack due to early stall onset at the flap. The DesignXplorer optimised solution matched that of the baseline solution very closely. The concept was seen to increase lift locally at the flap for both optimisation methods.

• 한국군사과학기술학회지
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• 제23권4호
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• pp.363-370
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• 2020

In this study, pitching stability derivatives of the conical shell configuration is predicted using commercial CFD code. Unsteady flow analysis with forced harmonic motion of the model is performed using overset mesh. The test is conducted about Basic finner missile configuration. The static and dynamic stability derivatives are good agreement with available experimental data. As the same way, a conical shell is analyzed in Mach number 1.6 and various reduced frequency. The static and dynamic derivatives are obtained from the time-pitching moment coefficient histories in each of four cases of mean angle of attack. The variation of reduced frequency is not affected static and dynamic derivatives. Increasing the mean angle of attack, static derivatives are increased slowly. Comparison of the Cm curves at the steady and unsteady state results shows that the Cm curve including the damping effect is lower than otherwise case, approximately 9-18 %.

• 한국시뮬레이션학회논문지
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• 제28권3호
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• pp.83-89
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• 2019

본 연구는 회전 비행체(Magnus rotor)를 탑재한 분산탄두의 분산 균일도에 미치는 요인 분석과 성능지표를 도출하기 위해 모탄의 속도 V와 회전속도 ${\omega}$, 비행경로각(flight path angle) ${\gamma}$ 그리고 고도 h의 변화에 따른 해석 결과를 기술했으며, 이때 모탄의 회전속도와 속도의 비를 새로운 변수로 정의했다. 자탄의 분산 해석에는 풍동실험을 통해 획득한 공력계수를 사용한 6 자유도 운동방정식을 이용했으며, 분산도 분석을 위해 회귀분석과 결정계수를 구해 분산도를 평가했다. 해석결과 최적의 회전속도와 낙하속도의 비, 비행경로각(flight path angle)을 구할 수 있었으며, 방출고도는 분산도에 회전속도와 낙하속도의 비, 비행경로각(flight path angle)의 영향에 비해 영향은 크지 않고, 자탄의 분산반경에 영향이 큰 것을 확인했다.

• Wind and Structures
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• 제36권2호
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• pp.105-120
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• 2023

The present study is performed to find the effect of corner recession on a square plan-shaped tall building. A series of numerical simulations have been carried out to find the two orthogonal wind force coefficients on various model configurations using Computational Fluid Dynamics (CFD). Numerical analyses are performed by using ANSYS-CFX (k-ℇ turbulence model) considering the length scale of 1:300. The study is performed for 0° to 360° wind angle of attack. The CFD data thus generated is utilised to fit parametric equations to predict alongwind and crosswind force coefficients, C_fx and C_fy. The precision of the parametric equations is validated by employing a wind tunnel study for the 40% corner recession model, and an excellent match is observed. Upon satisfactory validation, the parametric equations are further used to carry out multiobjective optimization considering two orthogonal force coefficients. Pareto optimal design results are presented to propose suitable percentages of corner recession for the study building. The optimization is based on reducing the alongwind and crosswind forces simultaneously to enhance the aerodynamic performance of the building.

• 한국전산구조공학회논문집
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• 제28권2호
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• pp.153-160
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• 2015

본 연구는 고층건축물의 기본설계 단계에서 평면형태를 결정할 때, 응용할 수 있도록 다양한 형상을 가진 고층건축물에 작용하는 풍력 및 풍응답에 대한 데이터베이스를 구축하는데 목적이 있다. 따라서 본 논문에서는 풍력데이터베이스의 초기단계로, 높이 200m이상의 고층건축물의 변장비(D/B=0.33, 0.50, 0.77, 0.83, 0.91, 1.0, 1.1, 1.2, 1.3, 2.0, 3.0) 변화에 따른 풍력의 특성을 조사하고 기존 문헌과의 비교 검토를 통해 실험결과를 검증하였다. 또한 풍하중조합의 관점에서 풍방향-풍직각방향, 풍방향-비틀림방향 및 풍직각방향-비틀림방향 간의 풍력의 상호상관에 대해서 검토하였다. 실험결과, 풍방향 및 풍직각방향에 대한 평균 및 변동 모멘트계수와 풍직각방향 및 비틀림방향 변동모멘트계수의 파워스펙트럼밀도의 결과는 기존 연구결과와 잘 부합되는 것으로 나타났다. 또한, 지표면조도의 변화에 따른 풍방향, 풍직각방향 및 비틀림방향에 대한 풍력의 특성은 큰 변화가 없는 것으로 나타났다. 시간영역과 주파수영역에서의 변동모멘트의 상호상관계수 분석결과, 풍직각방향-비틀림방향 변동모멘트계수의 상호상관계수가 높게 나타나는 경향을 보였다.

• 한국항공우주학회지
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• 제43권12호
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• pp.1035-1047
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• 2015

고고도 장기체공 축소형 전기 동력 무인기(EAV-2H+)용 프로펠러의 성능을 평가하기 위해 풍동시험과 전산해석을 수행하였다. 3종의 프로펠러에 대해 성능 곡선을 측정하고, 운용 조건을 평가하여 EAV-2H+에 적용 가능 여부를 판단하였다. 낮은 rpm 영역에서 성능 계수의 저하 경향을 확인하였다. 프로펠러 성능에 미치는 강체 천이 테이프 부착 효과를 측정하고 분석하였다. 상용 전산유체역학 코드를 사용한 성능 해석을 수행하여 시험과 해석의 추력계수-동력계수 선도가 잘 일치함을 확인하였다. 전진비에 따른 성능 계수를 비교하고 결과 차이에 기여하는 시험장치의 영향을 평가하였다. 시험에서 관찰된 낮은 rpm 영역의 성능 감소 경향을 transition SST 모델이 유사하게 모사함을 확인하였다. 낮은 레이놀즈수에 의한 깃 요소의 공력 성능 저하가 프로펠러 성능 감소의 주원인으로 분석되었다. 고고도 조건 해석으로부터 프로펠러 성능 저하를 확인하였다.

• 한국전산유체공학회지
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• 제21권2호
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• pp.12-24
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• 2016

The standard ${\kappa}-{\varepsilon}$ and realizable ${\kappa}-{\varepsilon}$ models are adopted to improve the prediction performance on the recirculating flow. In this paper, the backward facing step flows are used to assess the prediction performance of the recirculation zone. The model constants of turbulence model are obtained by the experimental results and they have a different value according to the flow. In the case of an isotropic flow situation, decaying of turbulent kinetic energy should follow a power law behavior. In accordance with the power law, the coefficients for the dissipation rate of turbulent kinetic energy are not universal. Also, the other coefficients as well as the dissipation coefficient are not constant. As a result, a suitable coefficients can be varied according to each of the flow. The changes of flow over the backward facing step in accordance with model constants of the ${\kappa}-{\varepsilon}$ models show that the reattachment length is dependent on the growth rate(${\lambda}$) and the ${\kappa}-{\varepsilon}$ models can be improved the prediction performance by changing the model constants about the recirculating flow. In addition, it was investigated for the curvature correction effect of the ${\kappa}-{\varepsilon}$ models in the recirculating flow. Overall, the curvature corrected ${\kappa}-{\varepsilon}$ models showed an excellent prediction performance.