• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.5
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• pp.1-8
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• 2002

The performance of MAV(Micro Air Vehicles) propellers is highly affected by the aerodynamic characteristics of a 2-D blade airfoil shapes. XFOIL is used to predict the lift and drag coefficients in low Reynolds Number flows. ARA-D 6%, which shows a good performance in low Reynolds Number regions, is selected as a blade airfoil. The 3-D propeller blade shape is optimized with the minimum energy loss condition, and the distribution of aerodynamic coefficients of ARA-D 6% is calculated. The designed optimal blade is compared with the Black Widow's propeller blade shape in the same conditions. The results indicate that the designed propeller installed in MAV can provide a good performance.

• 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.44 no.9
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• pp.759-768
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• 2016

Design and performance analysis of propeller for solar-powered HALE UAV, EAV-3 are conducted. Experiment points of design variables are obtained by using Design of Experiment(DOE) and Kriging meta-model is generated for objective and constraints function. The geometry of propeller is designed by evaluating the response surface with requirement and restrictions. The validity of the design is verified by meta-model based optimization. Computational analyses are carried out by using commercial CFD code and the results are compared with those from a design code and wind tunnel test. The results showed good agreement with predictions of the design code at the design altitude. Also, it is confirmed that the blockage effect due to the measurement device and support strut is included in the test data and the results including this effect compare well with the test data.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.46 no.9
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• pp.723-734
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• 2018

A structural weight estimation methodology for the multicopter design process is presented. In general, a multicopter is composed of an airframe, motors, propellers, battery and so on. Among these, the weight of motors, propellers and battery can be obtained from the weight trends with respect to design parameters. However, the structural weight is hard to be estimated due to the various configurations and design concepts of multicopters. Moreover, the airframe weights of most commercial multicopter products are not provided. Thus, an accurate airframe weight model is required for the reliable mutlcopter design process. Firstly, the standard configuration of multicopters is defined. Then, we proposed the structural weight estimation method using the number and diameter of propellers determined from the initial step of sizing process. Finally, we validated our suggested method using the commerical products.

• Proceeding of EDISON Challenge
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• 2016.11a
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• pp.15-18
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• 2016

본 연구는 조류발전 터빈의 블레이드 형상 최적화 해석 시스템 개발에 대한 사전연구의 일환으로 EDISON CFD의 프로펠러 단독성능 S/W와 SNUFOAM ShipMesh Advanced 자동격자생성기를 이용하여 조류발전 터빈 주위 유동장에 대한 수치해석을 수행하였다. TSR 조건 변화에 따라 수치해석을 수행하고 이에 대한 power, total coefficient를 동일한 조건에서 수행된 실험결과와 비교 검증하여 해석자의 신뢰도를 확인하였다. 또한, 블레이드 전체를 모델링한 full body 해석과 하나의 블레이드만을 모델링한 single body 해석 결과를 비교하여 경제적이면서 정도 높은 터빈 성능해석 프로세스를 제안하였다. 조류발전 터빈의 TSR 조건 변화에 따라 낮은 TSR 조건에서는 국부적 와동발생에 의해 $C_P$가 감소하는 것을 확인하였고 설계 TSR에서 가장 좋은 효율을 보임을 확인하였다. 이를 통해 suction side의 압력 분포, 팁 와동의 강도 등 성능개선을 위한 주요한 설계변수를 식별하였다.

• Journal of the Society of Naval Architects of Korea
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• v.31 no.3
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• pp.112-118
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• 1994

In this paper, statistical approach to prediction of A-weighted noise level in ship cabins. based on multiple linear regression analysis, is conducted. The best regression formula is composed of seven parameters of the deadweight, the type of ship, the location of engines and cabins, the type of deckhouse and the propeller skew angle. Verification work was carried out with other 210 cabins' data in 6 ships. As a result, the formula ensures the accuracy of 3 dB(A) in 77 % of cases.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.1
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• pp.37-46
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• 2014

This paper describes the conceptual design and development test procedure of a unmanned scaled-down personal air vehicle(PAV) with drive and flight dual mode capability. Trade studies on operational requirements led to the suggestion of a quad tilt prop platform which has nacelle tilt capability with multi rotor configuration. Motors for propeller propulsion and driving mechanism were integrated into a single nacelle, then they were implemented by nacelle tilt mechanism for conversion between the drive and the flight modes. Primary design parameters and initial specifications were confirmed through conceptual design, then functional tests were performed with the test platforms for the drive and the flight modes.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.1
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• pp.47-58
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• 2014

In this research, the initial sizing of a HALE(High Altitude Long Endurance) UAV which uses solar power and hydrogen fuel cell as an alternative energy was performed. Instead of a wing box type, a glider type was chosen since it is relatively easy to get a data thanks to many researches abroad. Maximum takeoff weight is around 150Kg and the propulsion system is composed of motor, propeller, solar cell, and hydrogen fuel cell which can be recharged through electrolysis. Maximum takeoff weight was estimated as aspect ratio, wing span, wing area change while considering energy balance of required energy which is necessary for flight during the entire day and available energy which can be taken from the solar cell.