• Journal of the Korea Institute of Military Science and Technology
• /
• v.24 no.2
• /
• pp.237-244
• /
• 2021

In recent years, the maturity of the technology for a high speed underwater vehicle using supercavitation increase, it is entering the stage of applied research for practical use. In this study, hydrodynamic performance of the supercavitating object was evaluated by using a Viscous-Potential based Boundary Element Method(VP-BEM). 27 models with different shape parameters such as body diameter, length and fore-body shape were considered. The process of the supercavity development of each model was simulated, and drag generated according to operating conditions such as changes in water depth was analyzed.

• Journal of the Korean Society of Visualization
• /
• v.21 no.2
• /
• pp.83-90
• /
• 2023

The shape of an airfoil is a critical factor in determining aerodynamic characteristics such as lift and drag. Aerodynamic properties of an airfoil have a decisive impact on the performance of various engineering applications, including airplane wings and wind turbine blades. Therefore, it is essential to analyze the aerodynamic characteristics of airfoils. Various analytical tools such as experiments, computational fluid dynamics, and Xfoil are used to perform these analyses, but each tool has its limitation. In this study, airfoil parameterization, image recognition, and artificial intelligence are combined to overcome these limitations. Image and coordinate data are collected from the UIUC airfoil database. Airfoil parameterization is performed by recognizing images from image data to build a database for deep learning. Trained model can predict the aerodynamic characteristics not only of airfoil images but also of sketches. The mean absolute error of untrained data is 0.0091.

• Wind and Structures
• /
• v.38 no.5
• /
• pp.341-354
• /
• 2024

This paper presents a theoretical method to deal with the aerodynamic performance and pitch optimization of the horizontal axis wind turbine blades at low wind speeds. By considering a blade element, the functional relationship among the angle of attack, pitch angle, rotational speed of the blade, and wind speed is derived in consideration of a quasi-steady aerodynamic model, and aerodynamic loads on the blade element are then obtained. The torque and torque coefficient of the blade are derived by using integration. A polynomial approximation is applied to functions of the lift and drag coefficients for the symmetric and asymmetric airfoils respectively, where specific expressions of aerodynamic loads as functions of the angle of attack (which is a function of pitch angle) are obtained. The pitch optimization problem is investigated by considering the maximum value problem of the instantaneous torque of a blade as a function of pitch angle. Dynamic pitch laws for HAWT blades with either symmetric or asymmetric airfoils are derived. Influences of parameters including inflow ratio, rotational speed, azimuth, and wind speed on torque coefficient and optimal pith angle are discussed.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.46 no.1
• /
• pp.1-9
• /
• 2018

Lambda wing type Unmanned Combat Aerial Vehicle(UCAV) which adopts Blended Wing Body(BWB) has relatively less drag and more stealth performance than conventional aircraft. However, Pitching moment is rapidly increased at a specific angle of attack affected by leading edge vortex due to leading edge sweep angle. Wind tunnel testing and numerical analysis were carried out with UCAV 1303 configuration on condition of 50 m/s of flow velocity, $-4^{\circ}{\sim}28^{\circ}$ of the range of angle-of-attack. The effect of wing twist for longitudinal stability at the various angles of attack was verified in this study. When negative twist is applied on the wing, Pitch-break was onset at higher angle of attack due to delayed flow separation on outboard of the wing. On the other hand, pitch-break was onset at lower angle of attack and lift-to-drag ratio was increased when positive twist is applied on the wing.

• Journal of the Korean Society of Fisheries and Ocean Technology
• /
• v.31 no.4
• /
• pp.340-349
• /
• 1995

There are several problems in a fishing by the midwater pair trawl net which is used in Denmark; steeply decreasing of the net height with the towing speed increasing, the larger volume of the fishing gear in comparison with the size of the trawler, and catching of a float in a mesh, etc. To prevent steeply decreasing of the net height with the towing speed increasing and catching of a float in a mesh, it is sometimes more useful to use the kite instead of floats. This paper describes the hydrodynamic drag and the opening efficiency of the midwater pair trawl net and the midwater kite pair trawl net obtained by the model test in the circulation water channel. The results can be summarized as follows; 1. The hydrodynamic drag of the midwater kite pair trawl net is about 0.7 times smaller than that of the midwater pair trawl net. 2. The net height, mouth area and filtering volume of the midwater kite pair trawl net are smaller then those of the midwater pair trawl net when the towing speed is below 2.5knots, almost the same at 2.7knots, and are larger over 3.0knots. The net width of the midwater kite pair trawl net is same as that of the midwater pair trawl net. 3. The shapes of net mouth of both net are an oval steeply flatted with the towing speed increasing. The filtering volume of the midwater kite pair trawl net is larger then that of the midwater pair trawl net by 3% at 3.0knots, 11% at 4.0knots, and 16% at 5.0knots respectively.

• International Journal of Highway Engineering
• /
• v.13 no.1
• /
• pp.185-195
• /
• 2011

Aircraft-related accidents cause mass casualties and major material damages. At present, runway-related accidents in our country account for 28% of all air accidents. Furthermore, internationally 33% of all air accidents is connected with runway. To prevent these accidents, FAA mandates the installation of aircraft rapid arresting system(ARAS) at the runway end safety areas which do not meet the FAA requirements. Even if the areas satisfy the conditions, FAA recommends the installation of ARAS to ensure the safety. In accordance of the international affairs, the domestic studies for ARAS are in progress and the legal formalities for domestic adoption of ARAS is under way. In this study, we analyzed the stopping distance, drag force, vertical force and tire penetration of runway overrun to assess the performance of ARAS reasonably by using two different kinds of analysis programs. The first is ARRESTOR program adopted by FAA, and the second is LS-DYNA which is available for 3-dimensional nonlineal dynamic analysis. As a result, analytically the stopping distances between two programs are similar. The drag force is rather different, but the tendencies are similar. Later on, the 3-dimensional simulation analysis considering various air-craft condition and properties of packaging materials is necessary. In addition, ongoing development of simulation analysis program is required for more accurate analistic results.

• Journal of the Korean Society of Costume
• /
• v.57 no.4 s.113
• /
• pp.173-187
• /
• 2007

The purpose of this study is to analyze the fetishist characteristics and the aesthetic values of glamour style based on the premise that fetishism is the theoretical root of glamour style expressed in fashion throughout history. The following results are from analysing fetishist characteristics of glamour style. First, luxury was analysed from an angle of commodity fetishism. Every culture develops images and stories that portray a world in which its ideals are realized: a paradise, a utopia, a golden age, etc. Consumer goods often serve as 'bridges to these ideals'. People thus can fantasize about owning the perfect life. Crucially, however, they must never get everything they picture. That is why luxuries often take on displaced meaning. Glamour gives the displaced meaning visual form, making it beautiful and real. Second, the attention on the glamour of luxury goods as a bridge to ideals is connected to the glamour icon who is simultaneously a consumer of these luxury goods and a producer of cultural goods. Glamour icons including the courtesan of the late 19th century, the actress of the 1930s' Hollywood golden age and today's celebrities appear to efface the traces of production and create fetishist images in culture. Through this artificial principle, the commodity-cum-glamour icon comes to life as a splendid image of spectacle. Third, masquerade and seduction were analysed from an angle of sexual fetishism. A magnificent image of masquerade as sexual fetishism is often equated with femininity, especially in Hollywood movies, because the artificial seduction of the feminine -namely glamour- can be effected by the absence or silence of being. That is to say, the aesthetic revelation of femininity coincides with the fleshing out of artificial signs. Masquerade and the seduction of the feminine are connected with glamour's artificial sensuality from this point. Fourth, since 1980's when homosexuality as sexual deviation resurfaced as a hot topic, sexual ambiguity and bisexual image have gained attention as perverse sexuality. Next came queer theory, which reduced gender itself to a matter of surface rather than depth. According to queer theory, gender itself can be revealed as a kind of drag act. Drag's imitative performance may reveal that womanliness is just about 'dragging up'. Queerness as a decadent play makes a connection with the wicked origins of glamour. From these characteristics, four aesthetic values were deduced: ostentatious luxury and mysterious idolatry by commodity fetishism, artificial sensuality and playful queerness by sexual fetishism.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2008.03a
• /
• pp.671-679
• /
• 2008

The effect of Pre-cooled Turbojet Engine installation and nozzle exhaust jet on Hypersonic Turbojet EXperimental aircraft(HYTEX aircraft) were investigated by three-dimensional numerical analyses to obtain aerodynamic characteristics of the aircraft during its in-flight condition. First, simulations of wind tunnel experiment using small scale model of the aircraft with and without the rectangular duct reproducing engine was performed at M=5.1 condition in order to validate the calculation code. Here, good agreements with experimental data were obtained regarding centerline wall pressures on the aircraft and aerodynamic coefficients of forces and moments acting on the aircraft. Next, full scale integrated analysis of the aircraft and the engine were conducted for flight Mach numbers of M=5.0, 4.0, 3.5, 3.0, and 2.0. Increasing the angle of attack $\alpha$ of the aircraft in M=5.0 flight increased the mass flow rate of the air captured at the intake due to pre-compression effect of the nose shockwave, also increasing the thrust obtained at the engine plug nozzle. Sufficient thrust for acceleration were obtained at $\alpha=3$ and 5 degrees. Increase of flight Mach number at $\alpha=0$ degrees resulted in decrease of mass flow rate captured at the engine intake, and thus decrease in thrust at the nozzle. The thrust was sufficient for acceleration at M=3.5 and lower cases. Lift force on the aircraft was increased by the integration of engine on the aircraft for all varying angles of attack or flight Mach numbers. However, the slope of lift increase when increasing flight Mach number showed decrease as flight Mach number reach to M=5.0, due to the separation shockwave at the upper surface of the aircraft. Pitch moment of the aircraft was not affected by the installation of the engines for all angles of attack at M=5.0 condition. In low Mach number cases at $\alpha=0$ degrees, installation of the engines increased the pitch moment compared to no engine configuration. Installation of the engines increased the frictional drag on the aircraft, and its percentage to the total drag ranged between 30-50% for varying angle of attack in M=5.0 flight.

• Journal of Aerospace System Engineering
• /
• v.16 no.6
• /
• pp.54-63
• /
• 2022

Recently, electric propulsion aircraft with various propeller mounting positions have been under construction. The position of the propeller relative to the wing can significantly affect the aerodynamic performance of the aircraft. Placing the propeller in front of the wing produces a complex swirl flow behind or around the propeller. The up/downwash induced by the swirl flow can alter the wing's local effective angle of attack, causing a change in the aerodynamic load distribution across the wing's spanwise direction. This study investigated the influence of the distance between a propeller and a wing on the aerodynamic loads on the wing. The swirl flow generated by the propeller was modelled using an actuator disk theory, and the wing's aerodynamics were analysed with the VSPAERO tool. Results of the study were compared to wind tunnel test data and established that both axial and spanwise distance between the propeller and the wing positively affect the wing's lift-to-drag ratio. Specifically, it was observed that the lift-to-drag ratio increases when the propeller is positioned higher than the wing.

• Journal of Navigation and Port Research
• /
• v.38 no.4
• /
• pp.335-341
• /
• 2014

Faced with global agenda of greenhouse abatement program including regulations and $CO_2$ emission trading scheme, shipping companies are enforced to a high level of efficiency in fuel consumption. Accordingly shipbuilding companies worldwide are required to develop fuel-efficient ships which otherwise traditionally consume a great amount of fossil fuels. In this dissertation, relevant to the improvement of fuel efficiency for commercial ships, design methodology through the numerical simulations are intensively described. This work consists of derivation of effective hydrodynamic design practice based on the application of longitudinal grooves to effectively improve the pressure distribution around ship hull. The primary objective of the present study is to improve ship resistance performance using longitudinal grooves which originate from long strips on the abdomen of humpback whale. Several groove shapes have been extensively investigated and the proposed shape efficiently controlled the variation of pressure distributions acting on the hull surface.