• Proceedings of the KSR Conference
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• 2009.05a
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• pp.1680-1686
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• 2009

Flow characteristics of a differential pressure flow meters which have a shape of triangular separate bar (TSB) was investigated according to machining conditions in pressure tapping holes. Size of pressure tapping holes is machined with either 1.0 mm or 1.5 mm in diameter. Also, number of pressure tapping holes are drilled either 9 or 17. The mass flow rate of the TSB flow meters are calibrated with a laminar flow meter by connecting them in line. The mass flow rate in the TSB flow meters are plotted with a non-dimensional parameter H which includes the gas temperature, exhaust gas pressure and differential pressure at the flow meters, and atmospheric pressure. An empirical correlation between the mass flow rate at the TSB flow meter and the non-dimensional parameter H was obtained. The empirical correlation showed highly linear relationship between the mass flow rate and the non-dimensional parameter H. The hole size of the pressure tapping holes has a bigger effect on the flow rate than the number of the tapping holes.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.5
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• pp.24-31
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• 2002

The effects of vortex generators, in the form of small delta-shaped tabs or thin tapes at an axi-symmetric supersonic nozzle exit, on the characteristics of supersonic jet flowfields are investigated by Schlieren images and Pitot-tube measurements. Small tabs as small as 1 % of the nozzle exit area can introduce streamwise vortices and produce a significant effect on the jet flowfield downstream of the nozzle. The effect is stronger for the cases of under-expanded jet than over- and perfect-expanded cases, introducing a larger flow entrainment. The effects of the angle of tabs with respect to the flow direction are also investigated, and for over-expanded jet cases, it is found that the tabs bended toward upstream can weaken the interaction strength and remove the Mach disc in the jet flowfield. Introduction of small proturbances inside the nozzle surface by attachment of thin tapes is also found to change the pressure distribution in the circumferential direction of the flowfield. Its effect is also found to be dependent on the jet expansion ratio.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.4
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• pp.73-79
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• 2004

An experimental and computational study has been performed for investigation of the jet interaction in supersonic flow with a ramp located behind a sonic, lateral jet. The experimental techniques include schlieren, pressure taps, and Pressure Sensitive Paint. The numerical solver used in this study is AeroSoft's structured flow solver GASP Version 4.0. A Mach 4 crossflow with a pressure ratio of 532, and the 3D ramp was designed by parametric study using GASP. The results showed that the ramp located downstream of the jet decrese the nose-down pitching moment by 70% without a force loss.

• Journal of the Korean Society of Marine Environment & Safety
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• v.27 no.5
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• pp.656-665
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• 2021

In this study, trim tabs were attached to end of stern hull of a small high-speed vessel of length approximately 10 m and Froude number 1.0 to improve resistance performance and passenger comfort. Before computational fluid dynamics (CFD) simulations to assess the performance according to various geometries of the trim tab, the scale effect had been found through a previous study, so full-scale simulations were performed. The trim tab chord length was set to 0.5 %, 1.0 % and 1.5 % of L_PP, and its angle to base line was varied in intervals of 5°. It decreased trim by stern and flotation: the greater the angle and length, the greater was the effect. Then it had pressure resistance decreased and shear resistance increased, and reduction ratio of total resistance varied accordingly. The results of this study indicated that the resistance performance was improved about 27 % at optimal running attitude that was the trim by stern about 1.5°.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.10
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• pp.934-939
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• 2007

Thrust vector control(TVC) is the method which generates the side force and moment by controlling the exhausting gas directly from the supersonic nozzle to change the trajectory of a missile quickly. In this paper, performance study on the tapered ramp tabs asymmetrically installed in the supersonic nozzle exhaust for the thurst vector control has been carried out using the supersonic cold flow system. To study the shock wave structure and location of the oblique shock wave produced by the ramp tab, the flow field visualization using the schlieren system is conducted. This paper provides the thrust spoilage, three directional forces and moments and distribution of surface pressure on the region enclosed by the tapered ramp tabs.

• 한국신재생에너지학회:학술대회논문집
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• 2011.11a
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• pp.74.2-74.2
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• 2011

석탄가스화 기술은 고온, 고압 조건에서 석탄과 산소의 불완전연소 및 가스화 반응을 통해 일산화탄소(CO)와 수소($H_2$)가 주성분인 합성가스를 제조하여 이용하는 현실적인 에너지원의 확보를 위한 방법인 동시에 이산화탄소를 저감할 수 있는 기술이다. 석탄가스화기 공급되는 석탄은 산소와의 부분 산화, 수증기 및 $CO_2$와의 반응에 의하여 합성가스로 전환되는데, 일반적으로 슬래깅 방식 석탄가스화기의 정상운전 중에 가스화기 내부 온도는 $1,400{\sim}1,600^{\circ}C$ 정도의 고온이며, 운전압력은 20~60 기압으로 매우 고압 상태에서 운전이 이루어지는데, 공급되는 석탄 시료의 성분들 중 가연성 물질의 99% 이상이 합성가스로 전환되는 반면, 회분에 해당되는 무기물의 대부분은 용융 슬랙 형태로 가스화기의 벽을 타고 흘러내리다가 슬랙탭을 통해 하부의 냉각조로 떨어지면서 급냉이 이루어지게 된다. 그러므로, 석탄가스화기 정상운전중 슬랙탭 주변의 온도를 고온으로 유지함으로써 용융슬랙의 고형화를 방지하는 것은 석탄가스화기의 안정적인 연속운전을 위하여 중요한 기술 중의 하나라고 할 수 있다. 따라서, 본 연구에서는 저급탄 가스화를 위한 1 톤/일급 고온, 고압 습식 석탄가스화기의 정상운전중 슬랙탭 부근에서 용융슬랙의 고형화를 방지하기 위한 슬랙탭 버너시스템의 설계를 진행하였으며, 안정적인 운전조건 도출을 위하여 보조연료(CNG)와 산소의 공급비율에 따른 화염특성 시험을 진행하였다.

• Journal of Adhesion and Interface
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• v.22 no.3
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• pp.85-90
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• 2021

Generally, the tensile strength of carbon fiber reinforced composite (CFRP) should be determined to produce this material. The tensile strength was performed based on ASTM D3039, and this test could cause the error by specimens and human. In this research, the CFRP tensile test was performed with different thickness of specimens and tap, adhesive for attaching tap, and pressure of jig to hold the specimens, while the test was performed based on ASTM D3039. The tensile stress and modulus exhibited differently with different specimen thicknesses, and the 1~1.5 mm thickness of the specimen was optimized. In the case of 0.28 MPa jig pressure, the slip or fracture at the clamping area of the specimen has not occurred, and specimens were fractured to the center section of the specimen. The adhesive to attach jig on specimen should be used to exhibit high adhesive stress. Experimental parameters could cause errors. It is expected to achieve an accurate tensile property evaluation of composite materials via improvements in adhesives, tabs, and jigs.

• Journal of the Korean Society of Propulsion Engineers
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• v.12 no.2
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• pp.33-39
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• 2008

To improve the mixing efficiency and to reduce the pressure loss, it is needed to develope a new mixing device for supersonic combustion. The vent mixer is introduced as the new supersonic fuel-air mixer. Computational analyses, that include pressure profile, density contour, and streamline tracing, have been carried out. The expansion wave generates at the end of the extended upper wall of the mixer. And it reduces the shock wave from the hole. Incoming air flow through the hole makes several recirculation regions which increase the mixing efficiency, and the separation region at the downward wall expends the boundary layer which reduces the pressure loss.

• Journal of the Korean Society of Manufacturing Technology Engineers
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• v.19 no.2
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• pp.204-210
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• 2010

The inner structure of the triangular separate bar (TSB) was improved to enhance the productivity of the TSB flow meter by simplifying the machining process for making the flow meter. The cross section of upstream and downstream pressure chamber in the TSB was changed from triangle to circle, which make it possible to substitute the wire cutting by drilling in the process of machining the pressure chamber. The flow rate characteristics of the flow meters was calibrated with a laminar flow meter. Six kinds of flow meters whose diameters of pressure tap for measuring pressure of both upsteam and downstream pressure chamber were different one another were made. The effects of the pressure tap diameter on the flow rate characteristics of the TSB flow meter was little. The mass flow rate characteristics of the flow meters with increasing a non-dimensional parameter which includes the gas temperature, exhaust gas pressure and differential pressure at the flow meters and atmospheric pressure shows nearly linear relationship with a correlation coefficient of R=0.998.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.40 no.3
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• pp.230-236
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• 2012

The purpose of this research is to determine the calibration constants of the wind speed measurement systems required to calculate the wind tunnel velocity in the test section. In the present work, the aerodynamic calibration tests of the test section were conducted in the Agency for Defense Development's Low-Speed Wind Tunnel. The test speed ranged from 10 to 100 m/s with a reference pitot-static pressure probe. The validity of the calibration results was evaluated by comparing them with the previous calibration constants. The calibration results show that fair to good agreement is obtained with resonable accuracy.