• Journal of Aerospace System Engineering
• /
• v.17 no.2
• /
• pp.45-55
• /
• 2023

This study conducted aeromechanics modeling and structural load analyses of Tilt Rotor Aeroacoustic Model (TRAM), a 25% scaled V-22 tiltrotor model used in wind tunnel tests. A rotorcraft comprehensive analysis code, CAMRAD II, was used. Analysis results of this study in low-speed forward flights were compared with DNW test and previous analysis results. Blade flap bending moments were in good agreement with measured data. Mean values and oscillatory loads for lead-lag bending and torsion moments were slightly different from measured data. However, when mean values were removed, results of structural loads for one rotor revolution were moderately compared with wind tunnel tests and previous analyses. Total forces and half peak-to-peak forces of the pitch link reasonably well matched with previous analysis results and measured data. Finally, harmonic magnitudes of blade structural loads were investigated.

• Journal of the KSME
• /
• v.51 no.6
• /
• pp.54-58
• /
• 2011

자동차용 풍동은 대부분 난류강도를 최대한 낮게 하여 시험의 재현성과 반복성을 극대화하도록 하였다. 그러나 최근 들어 뚜렷한 두 가지 흐름이 일고 있는데 지면재현과 실도로에서 경험하는 난류 강도를 풍동에서 재현하고자 하는 움직임이다. 이 글에서는 이러한 움직임의 이유와 방향에 대해 짚어보고자 한다.

• 한국신재생에너지학회:학술대회논문집
• /
• 2007.11a
• /
• pp.396-399
• /
• 2007

풍력 블레이드용으로 설계된 에어포일에 대하여 풍동 시험을 수행하였다. 설계된 에어포일의 레이놀즈수 범위에 맞추고자 코드 길이 40cm의 모델에 대하여 유속 17m/s, 35m/s, 50m/s에 대하여 에어포일 표면에서의 압력과 에어포일 뒤쪽 레이크에서의 압력을 측정하였다. 이를 통하여 설계에 사용된 기법의 타당성과 설계된 에어포일에 대하여 설계 변수에 대한 실질적 만족도에 대하여 평가하였다. 이와 더불어 표면 거칠기에 대한 모사를 위하여 트립도트를 부착하여 시험을 수행하였다. 이를 통하여 레이놀즈수와 표면 거칠기에 따른 에어포일의 성능 및 유동 변화 특성에 대하여 파악 할 수 있었다.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.32 no.9
• /
• pp.35-40
• /
• 2004

The high-speed wind tunnel test of rocket model was performed to investigate the effect of skirt configuration on aerodynamic load characteristics of nozzle. Test parameters were the length and diffusing angle of skirt. Test results showed that the gimbals actuator power could be reduced to 1/10 of that without skirt. The normalized test result was proposed to be used as database for skirt design.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2012.05a
• /
• pp.527-528
• /
• 2012

DBD (Dielectric Barrier Discharge) plasma actuator was designed for aerodynamic drag reduction using plasma flow control, and the drag reduction was measured by wind-tunnel tests using 2D test model. At the zero wind velocity, the plasma flow control had no effect on the drag reduction because the flow separation and surface friction drag were not occurred. At the wind velocity of 2m/s, 9.7% of drag was reduced by the flow separation control. The drag reduction decreased as the wind velocity increased.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.41 no.5
• /
• pp.335-341
• /
• 2013

The variation of systematic bias errors in the wind tunnel testing has been studied. A Design of Experiments(DOE) approach to an experimental study of fuselage drag and stability characteristics of a helicopter configuration was applied. When forces and moments measured in one time block differ significantly from measurements made in another time block under assumption that sample observations can be expected to yield same results within permissible measuring errors. The practical implication of this paper is that the systematic error can not be assumed not to exist. The those error reduction could be achieved through the process of randomization, blocking, and replication of the data points.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.33 no.10
• /
• pp.75-81
• /
• 2005

Jettison, grid and CTS test are widely used for the store and stage separation studies. This is an introductory paper on the experimental methodology and typical results of grid and CTS test used for the Korean 3-stage sounding rocket development. Thirteen separation trajectories were evaluated in the ONERA S2MA wind tunnel at Mach numbers of 2.0 and 2.8. The test result was applied as the basic database for the design of optimized separation device.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.36 no.4
• /
• pp.321-327
• /
• 2008

The shock tunnel as a hypersonic ground test facility was designed, constructed and its performance test was conducted to reproduce the high speed flow which the hypersonic propulsion system is encountered. The design points were understood and the conceptual design was completed using the quasi one dimensional operation analysis code. After that, the specific performance and compartment design were completed using CFD simulation as the part analysis. The facility was then constructed according to those design results and the performance test was conducted for various operation conditions. In this paper, we suggested the design method of hypersonic shock tunnel including the conceptual and performance design using theoretical analysis and the quasi 1D Multi-species computational fluid dynamics code.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.44 no.11
• /
• pp.933-940
• /
• 2016

A comparative study between a wind tunnel test and an XFOIL simulation looking at the aerodynamic performance of the airfoil for MW-class wind turbine was conducted for validation in the design stage. Tests are carried out for 21% and 30% thickness-ratio airfoils developed for 5 ~ 10 MW offshore wind turbine and the results are compared with the output from the XFOIL simulation at Reynolds number $1.0{\times}10^7$. The test is performed at a free-stream velocity of 50 m/s, corresponding to a Reynolds number of $2.2{\times}10^6$ based on the chord. Surface roughness is simulated using a zig-zag tape. Discrepancies between the results of the test and the XFOIL analysis are found, however, meaningful data for surface pressure distribution, basic performance and surface roughness effect are obtained from the tests, while useful lift-to-drag ratio data is found by the XFOIL simulation.

• Aerospace Engineering and Technology
• /
• v.5 no.2
• /
• pp.47-52
• /
• 2006

The external balance of KARl LSWT is installed by Aerotech at 1998. It has been used for more than 70 tests until 2004. The upgrade and re-calibration program are planed to solve the problem that revealed in 7-years operation and to increase the accuracy of the system. In this paper, 3 calibration results are presented. The first one is the results done by Aerotech at 1998, the second one is the results by using quick-loading system at 2004, and the last one is the results done at 2005.