• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.9
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• pp.816-822
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• 2011

In this study, a program has been coded to evaluate propeller thrust rapidly following the effects of propeller shapes and the environmental facts. At this time, Semi-infinite Helical Vortices model is used to predict the induction factor which is introduced by Kawada. This program is based on Wrench's Propeller lifting line theory, and it can predict aerodynamic coefficients such as thrust, power, and efficiency. First of all, this program is compared with test results of NACA reports to verify of the reliability. Secondly, subsonic wind tunnel test has been performed following variations of propeller's rpm and inflow velocities.

• Journal of the Society of Naval Architects of Korea
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• v.37 no.2
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• pp.22-29
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• 2000

The cavitation noised of high-speed propellers was experimentally studied in KRISO cavitation tunnel. In this paper, a series of cavitation noise tests were carried out for five propellers with various sections and loading distributions. From the experimental results, the noise characteristics of various cavitation pattern and the noise performance of the propellers were analyzed. There can be used for optimum design for high-speed propellers.

• Journal of the Korea Convergence Society
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• v.11 no.12
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• pp.131-135
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• 2020

In this study, the models with three, five and ten wings of the propeller which made a light aircraft fly were performed by air flow analyses. As for the flow model A with the shape with five wings, Model A can be seen to be the most ideal flow of air. The flow of air through the number of wings, which is not too many or too few, shows the most smooth flowing form. The smaller the number of propeller blades, the smaller the flow of air. Model A is applied under pressure of up to 0.5631 MPa at the front of air flow. Also, models B and C are applied under pressures of 0.5758 MPa and 0.5589 MPa, respectively. Comparing the pressure contours for each model of flux, model B can be shown to have the highest pressure distribution. The result of this study can be used to investigate the air flow without actual testing. It also seems to be helpful in the aesthetic convergent design of light aircraft propeller.

• Journal of the Korean Society of Marine Environment & Safety
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• v.30 no.1
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• pp.108-117
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• 2024

In this study, simulations based on computational fluid dynamics were performed for self-propulsion performance prediction of a catamaran that has asymmetrical inside and outside hull form and numerous knuckle lines. In the simulations, the Moving Reference Frame (MRF) or Sliding Mesh (SDM) techniques were used, and the rotation angle of the propeller per time step was different to identify the difference using the analysis technique and condition. The propeller rotation angle used in the MRF technique was 1˚ and those used in the SDM technique were 1˚, 5˚, or 10˚. The torque of the propeller was similar in both the techniques; however, the thrust and resistance of the hull were computed lower when the SDM technique was applied than when the MRF technique was applied, and higher as the rotation angle of the propeller per time step in the SDM technique was smaller in the simulations for several revolutions of the propeller to estimate the self-propulsion condition. The revolutions, thrust, and torque of the propeller in the self-propulsion condition obtained using linear interpolation and the delivered power, wake fraction, thrust deduction factor, and revolutions of the propeller obtained using the full-scale prediction method showed the same trend for both the techniques; however, most of the self-propulsion efficiency showed the opposite trend for these techniques. The accuracy of the propeller wake was low in the simulations when the MRF technique was applied, and slight difference existed in the expression of the wake according to the rotation angle of the propeller per time step when the SDM technique was applied.

• Proceedings of the Korean Society of Precision Engineering Conference
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• 1992.10a
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• pp.330-334
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• 1992

현재 제품의 보다 향상된 의장성과 기능성을 위해서 정밀한 자유곡면 형상의 제품에 대한 수요가 증가함에 따라 자유곡면 형상 제품의 효율적이고 정밀한 설계 및 가공과 함께 제품에 대한 수치 검사가 더욱 중요해지고 있다. 이러한 자유곡면 형상 제품의 예로는 금형, 헬리콥터 프로펠러, 비행기 날개 등이 있다. 이러한 제품의 설계 및 가공을 위해서 많은 CAD/CAM 시스템이 개발되었다. 수치 검사 분야에서는 기하학적으로 복잡한 제품에 대한 정밀하고 효율적인 검사를 위해서, 3차원 좌표측정기을 포함한 컴퓨터의 구동의 수치 검사 장비가 개발되고, 그러한 장비를 이용한 CAI 시스템사용이 다양한 분야에서 점차 증가하고 있다.

• Journal of the Society of Naval Architects of Korea
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• v.36 no.4
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• pp.28-36
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• 1999

An efficient inverse design method based on the MGM(Modified Garabedian-McFadden) method has been developed. The 2-D Navier-Stokes equations are solved for obtaining the surface pressure distributions and coupled with the MGM method to perform the inverse design. The MGM method is a residual-correction technique, in which the residuals are the difference between the desired and the computed pressure distribution. The developed code was applied to several airfoil shapes and the propeller. It has been found that they are well converged to their targeting shapes.

• Proceedings of the Korea Water Resources Association Conference
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• 2012.05a
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• pp.697-697
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• 2012

하나의 측선에 대해 3점법으로 세 지점의 유속을 동시에 측정할 수 있는 장치를 고안하였으며, '다수심 유속계'라 명명하였다. 본 장치는 5단의 관절부를 이용하여 등수심을 유지하며, 표면에서 수심을 측정하는 동시에 피그미 유속계를 이용하여 3지점의 유속 (V0.2, V0.6, V0.8)을 취득할 수 있다. 다수심 유속계의 현장 적용 실험을 실시하였다. 프로펠러 유속계와 다수심 유속계를 이용하여 유량을 측정한 결과, 거의 유사한 유량을 확인할 수 있었다. 하지만 측정시간의 경우 프로펠러 유속계는 약 1시간, 다수심 유속계는 약 30분으로 약 2배에 가까운 차이를 확인할 수 있었다. 한편 현재 개발 단계에 있는 다수심 유속계는 25cm 이상의 수심에서 3점자료 취득이 가능함으로써 하천 형상에 따른 유체 흐름 파악에 적합하며, 관측 자료의 신뢰도 향상에 기여할 수 있다고 판단된다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.11
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• pp.9-17
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• 2006

The SNU MAV has been designed through studies on highly efficient aerodynamic shape and propulsion system. The configuration of the vehicle was determined from conventional empirical equations, iterative wind tunnel tests and flight tests. The propeller shape was optimized with the various thrust tests and RSM(Response Surface Method) to obtain the higher efficient propulsion system. It was certified that the MAV could fly for over 17 minutes with a 210mAh battery. In addition, it showed good flight characteristics in both stability and controllability.

• Journal of the Society of Naval Architects of Korea
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• v.60 no.6
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• pp.416-423
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• 2023

Recently, the design point of the propeller is gradually changing due to the demand for energy saving and environmental protection. Until recently, self-propulsion model tests were conducted using stock propellers and geometry information was provided to propeller designers, but the range of existing stock propellers did not keep up with the changing design points, and the range of series propellers required in the initial design was also insufficient. Future propeller performance requires high performance and eco-friendliness, and the need for expansion of series propellers has increased. In order to respond to future needs and provide a wide range of advantages in propeller design, KRISO manufactures about 100 series propellers and builds series data through a model tests. In this paper, the approach method for deriving the representative optimal shape to be applied to the 4-blade series propeller in the initial stage of series propeller development was summarized.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.3
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• pp.173-184
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• 2013

A multi-level design optimization framework for aerodynamic design of rotary wing such as propeller and helicopter rotor blades is presented in this study. Strategy of the proposed framework is to enhance aerodynamic performance by sequentially applying the planform and sectional design optimization. In the first level of a planform design, we used a genetic algorithm and blade element momentum theory (BEMT) based on two-dimensional aerodynamic database to find optimal planform variables. After an initial planform design, local flow conditions of blade sections are analyzed using high-fidelity CFD methods. During the next level, a sectional design optimization is conducted using two dimensional Navier-Stokes analysis and a gradient based optimization algorithm. When optimal airfoil shape is determined at the several spanwise locations, a planform design is performed again. Through this iterative design process, not only an optimal flow condition but also an optimal shape of an EAV propeller blade is obtained. To validate the optimized propeller-blade design, it is tested in wind-tunnel facility with different flow conditions. An efficiency, which is slightly less than the expected improvement of 7% predicted by our proposed design framework but is still satisfactory to enhance the aerodynamic performance of EAV system.