• Journal of the Korean Society of Laryngology, Phoniatrics and Logopedics
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• v.7 no.1
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• pp.56-60
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• 1996

The vocal efficiency(VE) can be calculated as the ratio of acoustic power to aerodynamic power. It relates to the vocal intensity, air Sow rate and subglottic pressure. In this study, we treated 20 cases of vocal polyps and 10 cases of vocal nodules by way of laryngo-microsurgery or laser laryngo-microsurgery. The VE was measured preoperatively and postoperatively in all cases. The results showed that there was a significant improvement of VE postoperatively than that of preoperative measurement(p＜0.01) in vocal Polyp group. However, there was no significant difference(p＞0.05) in vocal nodule group. Through comparing the results, we obtained the conclusion : The laryngo-microsurgery is the reliable method of management for the vocal polyps, but f3r the vocal nodules, the laryngo-microsurgery should be selected after other more conservative approaches fail to produce the desired results.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.23 no.3
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• pp.1-7
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• 2015

In the present study, we conducted the research on the high efficiency propulsion system for the development of long-endurance UAV with an electric propulsion system. For the long endurance UAV, fair aerodynamic characteristics with the high efficiency of the propulsion system is required because the flight power and the duration time of the long-endurance UAV vary greatly depending on the efficiency of the propulsion system. Therefore, in this study, the tracking program which records the performance of motor, propeller was developed because of their wide variation in the efficiency depending on the using condition, and records from the existing flight test program were utilized to check the accuracy of the program we had developed. For the development of future long-endurance solar UAV, we confirmed the applied voltage of motor, the optimal rotation of propeller and the gear ratio of reduction gear in order to get the highest efficiency on the propulsion system at the optimal flying condition.

• Journal of Astronomy and Space Sciences
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• v.1 no.1
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• pp.5-21
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• 1984

The airflow along the surface of a launch vehicle together with base flow of clustered nozzles cause problems which may affect the stability or efficiency of the entire vehicle. The problem may occur when the vehicle is on the launching pad or even during flight. As for such problems, local steady-state loads, overall steady-state loads, buffet, ground wind loads, base heating and rocket-nozzle hinge moments are examined here specifically.

• 한국전산유체공학회:학술대회논문집
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• 2011.05a
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• pp.368-372
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• 2011

The aerodynamic characteristics of the L-type side jet thruster are examined by using computational fluid dynamics methods. The critical design points of L-type side jet thruster with bent nozzle by 90degrees are studied in terms of the relation between side jet nozzle geometry and thrust efficiency.

• 유체기계공업학회:학술대회논문집
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• 2003.12a
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• pp.482-486
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• 2003

A high-efficiency turbo steam compressor has been successfully developed for the MVR desalination system, first one in Korea. The state-of-the-art design methods using real gas properties were applied to get all the aerodynamic design results. Bull and pinion gear trains, tilting-pad bearings and investment cast impellers were developed also to be integrated into the integral gear-driven turbo steam compressor. System tests show highly efficient performance.

• 한국연소학회:학술대회논문집
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• 2015.12a
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• pp.277-278
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• 2015

Korea Aerospace Research Institute(KARI) has developed the gas turbine core technologies since 1989 and has built the infrastructure for the development of gas turbine. Efficiency and flow instability are the major research object in radial and axial compressors. For combustor, NOx reduction is major research object. KARI also has developed turbine cooling technology as well as turbine aerodynamic technology.

• 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.

• Journal of the Korean Society of Laryngology, Phoniatrics and Logopedics
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• v.10 no.1
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• pp.5-11
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• 1999

Background and Objectives : Recently, many people suffering from voice change visit otolaryngologist. So, it is important to study vocal function in patients with glottic or laryngeal disease. Aerodynamic investigation is valuable information about the efficiency of the larynx in translating air pressure to acoustic signal. The purpose of this study was to investigate the aerodynamic data in patients with vocal polyp, compare this data with that of the normal Korean. Materials and Methods : In aerodynamic study, maximum phonation time, mean air flow rate, phonatory flow volume and subglottal pressure were tested by using Aerophone II voice function analyzer in 157 normal korean and 143 patients with vocal polyp, aged from 20 to 69 years randomly selected. Results and Conclusion : In vocal polyp, maximum phonation time was significantly decreased and mean air How rate was increased. Phonatory flow volume was significantly decreased and subglottic pressure was increased only in female with vocal polyp. These data will be served as basic data of evaluation after treatment and postoperative assessment of the patients with vocal polyp.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.48 no.5
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• pp.335-342
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• 2020

Tailless aircraft designed for stealth efficiency uses spoilers instead of rudders for the directional control. When the spoiler is rapidly deployed, highly nonlinear and unsteady aerodynamic characteristics can be generated, resulting in adverse effects on aircraft flight performance. This paper investigates the aerodynamic characteristics of an airfoil with moving spoiler using dynamic mesh CFD technique. The effects of spoiler operation speed, mounting location, and deployment scheduling are analyzed to reduce the adverse effects of the spoiler's dynamic operation. The results shows that the adverse effects of dynamic spoiler can be reduced by appropriate selection of the spoiler mounting location and deployment scheduling.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.46 no.2
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• pp.95-105
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• 2018

Increasing cruise speed is an important issue for the development of the next generation rotorcraft. Among several concepts proposed by previous research, the rotorcraft with ducted fan demonstrates its possibility of high-speed flight. In this study, numerical simulations are conducted to investigate the aerodynamic and flow characteristics of multi-ducted fan in forward flight. The aerodynamic efficiency around front ducted fan is determined by interaction between free-stream velocity and the induced velocity. While flow characteristics of rear ducted fan are dominantly influenced by the front ducted fan. Separation in the front ducted fan occurs faster than that of rear ducted fan, and the separation at duct inlet induces an increase of fan thrust. As a result of interaction effect between each ducted fan, relatively aligned inflow enters to the rear ducted fan. Therefore, thrust of the rear fan is decreased steadily before separation, and sudden changes of thrust in fans occur simultaneously. Due to the pressure decrease on lower surface, the normal force of rotorcraft is reduced with forward speed.