• 한국항공우주학회지
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• 제49권11호
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• pp.901-907
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• 2021

본 연구에서는 다양한 유도탄 노즈 형상과 유동조건에 대한 공력계수를 예측할 수 있는 인공신경망 기반의 공력 산출 기법을 제시한다. Missile DATCOM를 통해 유도탄 노즈 형상, 유동조건, 유도탄 공력계수로 구성된 학습 데이터셋을 구축하였다. 인공신경망의 예측 성능을 향상시키기 위해 데이터 전처리 과정으로 데이터 정규화를 진행하였고, 과대적합을 방지하기 위해 신경망 학습 과정 중 드롭아웃 기법을 사용하였다. 신경망을 통해 학습하지 않은 유도탄 노즈 형상과 유동조건에 대한 공력계수를 예측하였고 이를 Missile DATCOM 해석 결과와 비교하여 신경망의 성능을 검증하였다. 그 결과 본 연구에서 구축한 신경망은 학습하지 않은 유도탄 노즈 형상과 유동조건에 대한 유도탄 공력계수를 정확하게 산출할 수 있음을 확인하였다.

• Wind and Structures
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• 제24권5호
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• pp.405-430
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• 2017

The aerodynamic characteristics of vehicles are critical to assess vehicle safety and passenger comfort for vehicles running on long span bridges in a windy environment. However, in previous wind-vehicle-bridge (WVB) system analysis, the aerodynamic interference between the vehicle and the bridge was seldom considered, which will result in changing aerodynamic coefficients. In this study, the aerodynamic coefficients of a high-sided truck on the ground (ground case) and a typical bridge deck (bridge deck case) are determined in a wind tunnel. The effects of existent structures including the bridge deck and bridge accessories on the high-sided vehicle's aerodynamic characteristics are investigated. A three-dimensional analytical framework of a fully coupled WVB system is then established based on the finite element method. By inputting the aerodynamic coefficients of both cases into the WVB system separately, the vehicle safety and passenger comfort are assessed, and the critical accidental wind speed for the truck on the bridge in a windy environment is derived. The differences in the bridge response between the windward case and the leeward case are also compared. The results show that the bridge deck and the accessories play a positive role in ensuring vehicle safety and improving passenger comfort, and the influence of aerodynamic interference on the response of the bridge is weak.

• 대한토목학회논문집
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• 제26권5A호
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• pp.887-899
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• 2006

본 연구의 목적은 교량 거더 단면의 공기역학적 특성을 나타내는 기본 자료인 공기력계수와 플러터계수가 동적응답과 어떠한 상관관계를 가지는지를 규명하는데 있다. 이를 위해 세 단계의 단면모형실험이 수행되었다. 첫 번째 단계에서는 총 7개의 거더 단면 즉, 6개의 플레이트거더 단면과 1개의 박스거더 단면이 고려되었으며 거더 단면의 기하학적 형상, 영각, 바람의 방향 그리고 기류조건이 공기력계수인 항력계수, 양력계수 그리고 모멘트계수에 미치는 영향을 정적 단면모형실험을 통해 살펴보았다. 두 번째 단계에서는 동적실험을 통해 각 단면의 공기력계수와 동적응답의 상관성을 검증하였다. 마지막으로 2자유도하의 동적 단면모형실험을 통해 세 개의 거더 단면의 플러터계수를 산출하고 이를 동적실험결과와 비교하였다. 주어진 단면형상에 대한 비정상 공기력에 의해 변화되는 시스템의 감쇠와 강성을 가장 잘 반영하는 플러터계수는 초기변위-자유진동시스템을 이용하여 추출하였다. 이를 위해 등류조건에서 풍속별로 교량단면의 수직 및 비틀림 초기변위의 시간에 따른 진폭의 감쇠를 측정하였다. 본 연구에서 제시한 교량단면의 공기력계수와 플러터계수는 공탄석해석 및 버펫팅해석을 위한 기본 자료로 유용하게 쓰일 것으로 보인다.

• Wind and Structures
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• 제24권2호
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• pp.145-169
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• 2017

The auxiliary structures of a high-rise building, such as balconies, ribs, and grids, are usually much smaller than the whole building; therefore, it is difficult to simulate them on a scaled model during wind tunnel tests, and they are often ignored. However, they may have notable effects on the local or overall wind loads of the building. In the present study, a series of wind pressure wind tunnel tests and high-frequency force balance (HFFB) wind tunnel tests were conducted on rigid models of an actual super high-rise building with vertical ribs protruding from its facades. The effects of the depth and spacing of vertical ribs on the mean values, fluctuating values and the most unfavorable values of the local wind pressure coefficients were investigated by analyzing the distribution of wind pressure coefficients on the facades and the variations of the wind pressure coefficients at the cross section at 2/3 of the building height versus wind direction angle. In addition, the effects of the depth and spacing of vertical ribs on the mean values, fluctuating values and power spectra of the overall aerodynamic force coefficients were studied by analyzing the aerodynamic base moment coefficients. The results show that vertical ribs significantly decrease the most unfavorable suction coefficients in the corner recession regions and edge regions of facades and increase the mean and fluctuating along-wind overall aerodynamic forces.

• 한국항공우주학회지
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• 제49권2호
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• pp.95-106
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• 2021

측방제트는 조종면에 비해 즉각적인 유도무기 기동이 가능하지만 자유류를 간섭하여 공력계수에 영향을 줄 수 있다. 공력계수에 대한 측방제트의 영향을 파악하기 위해 측방제트를 공기로 모사한 후 측방제트 유무에 따른 공력계수 차이를 다충실도 모형을 사용하여 살펴본다. 측방제트 유무에 따라 공력계수 예측 모형으로 추정된 공력계수 간 차이를 계산하여 측방제트의 영향을 마하수, 뱅크각, 받음각의 변화에 따라 조사한다. 분석 결과, 종방향 힘 및 모멘트 계수는 비대칭적으로 발달한 측방제트에 큰 영향을 받았으며, 횡방향 힘 및 모멘트 계수는 -30°와 +30° 사이 뱅크각에서 최대로 변동하였다. 이에 반해 축방향 힘 계수는 측방제트에 영향을 받지 않았으며, 축방향 모멘트 계수는 마하수 변화에 대한 표본 부족으로 측방제트의 영향을 판단하기 어려웠다. 종합하면 측방제트가 종방향 및 횡방향 공력계수에 주요한 영향을 주어 유도무기 자세 변화를 일으킨다는 것을 확인하였다.

• Advances in aircraft and spacecraft science
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• 제2권4호
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• pp.427-443
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• 2015

The present paper is the follow-on of a former work in which the influence of the gas-surface interaction models was evaluated on the aerodynamic coefficients of an aero-space-plane and on a section of its wing. The models by Maxwell and by Cercignani-Lampis-Lord were compared by means of Direct Simulation Monte Carlo (DSMC) codes. In that paper the diffusive, fully accommodated, semi-specular and specular accommodation coefficients were considered. The results pointed out that the influence of the interaction models, considering the above mentioned accommodation coefficients, is pretty strong while the Cercignani-Lampis-Lord and the Maxwell models are practically equivalent. In the present paper, the comparison of the same models is carried out considering the dependence of the accommodation coefficients on the angle of incidence (or partial accommodation coefficients). More specifically, the normal and the tangential momentum partial accommodation coefficients, obtained experimentally by Knetchel and Pitts, have been implemented. Computer tests on a NACA-0012 airfoil have been carried out by the DSMC code DS2V-64 bits. The airfoil, of 2 m chord, has been tested both in clean and flapped configurations. The simulated conditions were those at an altitude of 100 km where the airfoil is in transitional regime. The results confirmed that the two interaction models are practically equivalent and verified that the use of the Knetchel and Pitts coefficients involves results very close to those computed considering a diffusive, fully accommodated interaction both in clean and flapped configurations.

• Wind and Structures
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• 제25권5호
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• pp.475-492
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• 2017

Inclined and yawed circular cylinder is an essential element in the widespread range of structures. As one of the applications, cables on bridges were reported to have the possibility of suffering a kind of large amplitude vibration called dry galloping. In order to have a detailed understanding of the aerodynamics related to dry galloping, this study carried out a set of wind tunnel tests for the inclined and yawed circular cylinders. The aerodynamic coefficients of circular cylinders with three surface configurations, including smooth, dimpled pattern and helical fillet are tested using the force balance under a wide range of inclination and yaw angles in the wind tunnel. The Reynolds number ranges from $2{\times}10^5$ to $7{\times}10^5$ during the test. The influence of turbulence intensity on the drag and lift coefficients is corrected. The effects of inclination angle yaw angle and surface configurations on the aerodynamic coefficients are discussed. Adopting the existed the quasi-steady model, the nondimensional aerodynamic damping parameters for the cylinders with three kinds of surface configurations are evaluated. It is found that surface with helical fillet or dimpled pattern have the potential to suppress the dry galloping, while the latter one is more effective.

• Wind and Structures
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• 제6권1호
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• pp.53-70
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• 2003

Tsing Ma Bridge in Hong Kong is the longest suspension bridge in the world carrying both highway and railway. It has two H-shape concrete towers, each of which is composed of two reinforced concrete legs and four deep transverse prestressed concrete beams. A series of wind tunnel tests have been performed to measure the aerodynamic coefficients of the tower legs and transverse beams in various arrangements. A 1:100 scaled 3D rigid model of the full bridge tower assembled from various tower components has been constructed for different test cases. The aerodynamic coefficients of the lower and upper segments of the windward and leeward tower legs and those of the transverse beams at different levels, with and without the dummy bridge deck model, were measured as a function of yaw wind angle. The effects of wind interference among the tower components and the influence of the bridge deck on the tower aerodynamic coefficients were also investigated. The results achieved can be used as the pertinent data for the comparison of the computed and field-measured fully coupled buffeting responses of the entire bridge under yaw winds.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2006년도 추계 학술대회논문집
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• pp.41-46
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• 2006

When new weapons are introduced, the target points estimation is one of the important objectives in the flight test as well as the safe separation. The prediction methods help to design the flight test schedule. However, the incremental aerodynamic coefficients in the aircraft flow field so-called BSE are difficult to predict. Generally, the semiempirical methods such as the grid methods, IFM and Flow TGP using database are used for estimation of BSE. However, these methods are quasi-steady methods using static aerodynamic loads. Nowadays the time-accurate CFD method is often used to predict the store separation event. In the current process, the incremental aerodynamic coefficients in BSE regime are calculated directly, and the elimination of delta coefficients is checked simultaneously. This stage can be used for the initial condition of Flow TGP with freestream database. Two dimensional supersonic and subsonic store separation problems have been simulated and incremental coefficients are calculated. The results show the time when the store gets out of BSE region.

• Wind and Structures
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• 제22권5호
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• pp.573-594
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• 2016

Simultaneous pressure measurements on 2D square prisms with various corner modifications were performed in uniform flow with low turbulence level, and the testing Reynolds numbers varied from $1.0{\times}10^5$ to $4.8{\times}10^5$. Experimental models were a square prism, three chamfered-corner square prisms (B/D=5%, 10%, and 15%, where B is the chamfered corner dimension and D is the cross-sectional dimension), and six rounded-corner square prisms (R/D =5%, 10%, 15%, 20%, 30%, and 40%, where R is the corner radius). Experimental results of drag coefficients, wind pressure distributions, power spectra of aerodynamic force coefficients, and Strouhal numbers are presented. Ten models are divided into various categories according to the variations of mean drag coefficients with Reynolds number. The mean drag coefficients of models with $B/D{\leq}15%$ and $R/D{\leq}15%$ are unaffected by the Reynolds number. On the contrary, the mean drag coefficients of models with R/D=20%, 30%, and 40% are obviously dependent on Reynolds number. Wind pressure distributions around each model are analyzed according to the categorized results.The influence mechanisms of corner modifications on the aerodynamic characteristics of the square prism are revealed from the perspective of flow around the model, which can be obtained by analyzing the local pressures acting on the model surface.