• 한국해양학회지:바다
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• 제12권4호
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• pp.251-261
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• 2007

본 연구에서는 경기만 근해 - 격렬비도와 덕적도 해역을 중심으로 - 에서 관측된 파랑 및 바람자료를 이용하여 바람과 파랑의 상호작용을 연구하였다. 2005년 1월에서 12월의 덕적도 부이 관측자료를 바탕으로 바람에 의한 파랑의 발생과 또 발생된 파랑에 의한 바람의 감쇄효과를 계산하였으며, 2005년 3월 19-26일과 5월 23-28일에 격렬비도 근해에서 관측된 자료를 이용하여 파랑이 발달할 때와 잔잔한 상태가 유지 될 때를 나누어 파랑 스펙트럼의 반응형태를 알아보았다. 또한, 시간에 따른 스펙트럼의 형태, 최대 에너지 주파수, 평형 영역의 기울기 등도 분석하였다. 관측풍속 $5-10ms^{-1}$의 범위에서 파랑에 의한 풍속의 감소는 최대 $2ms^{-1}$(응력${\sim}0.1Nm^{-2}$)를 보였고, $10-15ms^{-1}$일 때는 $3ms^{-1}$(응력${\sim}0.4Nm^{-2}$)의 차이를 보였다. 풍속과 파고의 상관분석에서도 관측풍속과 파고의 영향을 고려한 풍속(참풍속)의 경우 선형적인 상관도가 0.71에서 0.75로 약 0.04 정도 상승하였다. 잔잔한 상태에서 파랑이 발생할때 초기에는 4-5초의 단주기 파랑이 형성되고 발달과정을 거치면서 9-10초 주기의 장주기로 이동하며, 최대 에너지 주파주는 일정한 값을 유지하게 된다. 이 상태에 도달하는데 소요되는 시간은 약 6-7시간 정도였다. 또한 스펙트럼의 평형 영역 기울기는 파랑발생 초기에는 변화폭이 존재하나 풍파가 발달하면서 약 4.11의 값으로 접근하였다. 파랑 스펙트럼의 주파수대별 시간 변동과 마찰 속도와의 상관성에 있어 파랑 스펙트럼의 최대 에너지 주파수대 부근에서 높은 상관성을 보이는 경향을 보였으며 0.3 Hz와 0.35 Hz 에서 평균 0.80과 0.82 상관도를 보였다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년 영문 학술대회
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• pp.671-679
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• 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.

• 한국표면공학회지
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• 제53권6호
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• pp.271-279
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• 2020

Non-ferrous metals, widely used in the mechanical industry, are difficult to machine, particularly by drilling and tapping. Since non-ferrous metals have a strong tendency to adhere to the cutting tool, the tool life is greatly deteriorated. Diamond-like carbon (DLC) is one of the promising candidates to improve the performance and life of cutting tool due to their low frictional property. In this study, a sacrificial DLC layer is applied on the hard nitride coated drill tool to improve the durability. The DLC coatings are fabricated by controlling the acceleration voltage of the linear ion source in the range of 0.6~1.8 kV. As a result, the optimized hardness(20 GPa) and wear resistance(1.4 x 10-8 ㎣/N·m) were obtained at the 1.4 kV. Then, the optimized DLC coating is applied as an sacrificial layer on the hard nitride coating to evaluate the performance and life of cutting tool. The Vickers hardness of the composite coatings were similar to those of the nitride coatings (AlCrN, AlTiSiN), but the friction coefficients were significantly reduced to 0.13 compared to 0.63 of nitride coatings. The drilling test were performed on S55C plate using a drilling machine at rotation speed of 2,500 rpm and penetration rate of 0.25 m/rev. The result showed that the wear width of the composite coated drills were 200 % lower than those of the AlCrN, AlTiSiN coated drills. In addition, the cutting forces of the composite coated drills were 13 and 15 % lower than that of AlCrN, AlTiSiN coated drills, respectively, as it reduced the aluminum clogging. Finally, the application of the DLC sacrificial layer prevents initial chipping through its low friction property and improves drilling quality with efficient chip removal.