• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.6
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• pp.31-38
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• 2005

Aerodynamic influence coefficient linearly relates pressure with downwash in panel method for load analysis in which the viscosity of a flow is ignored and the compressibility cannot be taken into account in transonic region. Since the planform of an aerodynamic surface determines the coefficient, the panel method has a limit to the analysis of low Reynolds number flow. The accuracy of the pressure distribution can be improved by a direct correction to the pressure or a correction to the downwash, which is considered the change of camber or thickness, using the aerodynamic coefficients from wind tunnel test as constraints. A premultiplying correction method as well as a postmultiplying correction method is applied to a micro air vehicle to provide more accurate aerodynamic pressure for trim and load analyses. Theoretical aerodynamic pressure is obtained from the panel method. Correction factor matrix and correct pressure coefficient are computed for the conditions with two constraints in addition to single constraint. The postmultiplying correction method gives a better improvement in pressure distribution on micro air vehicle due to the flow characteristics on it.

• 유체기계공업학회:학술대회논문집
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• 2000.12a
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• pp.226-235
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• 2000

Two representative finite volume methods, i.e., the time marching method and the pressure correction method, were applied to 8 centrifugal compressor impeller flows, with low to very high level of pressure ratio, among which 7 impellers' experimental performance is given in the open literature. The present study is focused on the prediction differences from both methods, developed by the authors, in the pressure correction method's point of view. In all cases, the time marching method gives a satifactory solution, but the pressure correction method does not. Up to about $18\%$ less level of total-to-total pressure ratio is predicted by the pressure correction method as the level of the impeller pressure ratio increases up to about 10. The drop of total pressure ratio is caused by the underestimation of static pressure rise which seems to be attributed to inappropriate linearization and discretization of the pressure/density coupling terms in the pressure correction equation.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.21 no.11
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• pp.1437-1448
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• 1997

Pressures of a five-hole probe were measured for a full range of yaw and pitch angles and complete pressure coefficient maps were obtained. Based on these maps, various features of five-hole probe pressures were revealed and new five-hole probe calibration coefficients were devised. The new calibration coefficients show non-diverging characteristics for any flow direction and one-to-one correspondence for a wide range of flow angles. These calibration coefficients expand the valid flow angle range of five-hole probe calibration by .+-.10 degrees and complement a critical defect of five-hole probe zone-division calibration method which has not been known yet. Moreover new non-diverging calibration coefficients have advantages in nulling methods, too.

• Journal of the Korean Society of Propulsion Engineers
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• v.10 no.4
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• pp.61-68
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• 2006

To measure burning rate of solid propellants using ultrasound, a special closed bomb and an ultrasonic and pressure measurement system are fabricated. During pressurization tests and homing tests on propellants, ultrasonic and pressure signal are acquired in real time fashion by this system. Based on acquired signals, analysis programs using two different algorithm which can measure burning rates corresponding to pressures are compared. One algorithm is to correct sound velocity variation of propellants and solid couplant, another one is only to correct sound velocity variation of propellants. And accuracies of homing rates measured through these algorithms are calculated through comparison with the burning rates measured using strand burner method.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.259-265
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• 2005

To measure burning rate of solid propellants using ultrasonic technique, a special closed bomb and an ultrasonic and pressure measurement system are fabricated. During pressurization tests and burning tests on propellants, ultrasonic and pressure signal are acquired in realtime fashion by this system. Based on acquired signals, analysis programs using two different algorithm which can measure burning rates corresponding to pressures are compared. One algorithm is to correct sound velocity variation of propellants and solid couplant, another one is only to correct sound velocity variation of propellants. And accuracies of homing rates measured through these algorithms are calculated through comparison with homing rates measured using strand burner method.

• Transactions of the Korean Society of Pressure Vessels and Piping
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• v.7 no.1
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• pp.41-47
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• 2011

Residual stress is the key parameter for reliability and lifetime assessment because it can reduce the fatigue strength and fracture properties of industrial structures. Recently, instrumented indentation testing (IIT) has been widely used for evaluating it, since it does not need specific specimen and time-consuming procedure. However, conventional Oliver-Pharr method, which is used for calibrating contact depth to analyze indentation load-depth curve, cannot estimate plastic pile-up between indenter and surface of specimen. Here, we introduce f parameter which is the ratio of contact depth and maximum depth, to consider pile-up height. And, its application for evaluating residual stress of weldment is introduced.

• Journal of the KSME
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• v.19 no.2
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• pp.98-105
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• 1979

이상의 고압중스트레인 측정실험으로부터 다음과 같은 결론을 얻었다. (1) 고압중에서 스트레인을 측정할 경우, 압력효과스트레인이 생기므로 스트레인의 지시치를 보정할 필요가 있다. (2) 고압 효과스트레인은 같은 종류의 게이지에 있어서도 흩어짐이 있으나 흩어짐의 폭은 압력효과스트 레인의 값보다 작다. 특히 300 기압이상에서는 브릿지의 평형을 취해가지고 측정하며는 이 흩 어짐은 한결 작아진다. (3) 고압수중에서 측정 할 경우, 대후론, 시리콘고무, 이중피복선을 도선 으로 하여 사용하고, 게이지의 부분은 시리콘고무코우팅을 되도록 두껍게 하며는 3,000 기압 정 도까지의 수압중에서도 절연저하를 초래하지 안고, 스트레인측정을 할 수가 있다. (4) 상기의 절연방법은 도선인출부에도 적용할 수 있다. (5) 원통형 하우징 모형의 내외면의 스트레인를 측 정한 결과, 유한요소법해석결과의 타당성을 확인 할 수가 있었다. 본실험은 1974년도 일본통산 성공업기술원에서 위탁받아 동지종합연구소에서, [대식도 원읍조작해저석유굴삭장치의 개발]에 관한 연구성과의 일부와 Waterloo 대학의 G.S. Kular 교수연구실의 연구결과임을 밝혔다.

• Journal of the Korean Society for Nondestructive Testing
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• v.28 no.1
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• pp.1-8
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• 2008

The object of this study is to develop the examination technique for measuring the O-ring deformation behavior under the pressure and the squeezed condition simultaneously. The O-ring deformation measuring device in which two grooves were dug to insert the two O-rings was manufactured to be not deformed under the high pressure and the 1 mm and 0.1 mm gap were designed to measure the extrusion lengths under the internal pressure. The beam hardening correction, the histogram analysis and the dead zone correction were executed to exactly measure the shape of O-ring deformation and the lengths of the O-ring deformation were measured by the LSF and the ERF. The computed tomography applied the pressure of 0, 1.378, 4.902, 9.804, 15.692 MPa at 22.3% squeezed condition and the expanded diameter, contact length and extrusion depth were measured in each pressure. The shape of O-ring deformation was evaluated by the FEM to verify the results of measuring by the computed tomography and the area of O-ring was mutually compared to the area measured by the computed tomography.

• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• 2011.11a
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• pp.94-95
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• 2011

선박 엔진 크랭크 케이스 내부의 기계 결함으로 발생하는 윤활 오일 미스트 발생은 폭발뿐만 아니라 급격한 온도와 압력상승으로 2차 폭발을 야기하는 등 큰 피해를 가져와 현재 선박용 엔진의 크랭크 케이스에 오일미스트 검출장치의 설치를 의무화 하고 있는 추세이다. 본 논문에서는 이러한 피해를 줄이기 위하여 광 산란 방식을 이용한 오일 미스트 검출장치를 구현하였으며, 구현된 오일미스트 검출 장치의 오일미스검출 센서 센싱 성능은 전기적, 광학적 그 외 환경적 요인으로 인하여 출력값이 일정하지 못해 각각의 오일미스트 검출 센서를 보정해야 한다. 본 논문에서는 크랭크케이스마다 장착되는 오일미스트 검출 센서의 오차를 최소화하기 위하여 정밀하게 Calibration된 Reference Data를 기반으로 최소자승법을 적용하여 센서를 Calibration하였으며, 그 결과 각각의 오일미스 검출센서의 오차를 기존 방법과 비교하여 최소화할 수 있었다.

• Journal of Energy Engineering
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• v.6 no.1
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• pp.52-57
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• 1997

Dynamic characteristics of compressible flow fields in super-circled constricted tube have been studied numerically. By applying MacCormack's explicit scheme, time marching method with predictor/corrector step, Euler equation is solved to find characteristics of fluid flow in a constricted tube where a two-dimensional inviscid compressible flow is assumed. The effects of tube diameter and aspect ratios on the pressure variations are discussed extensively. The results of the developed numerical schemes are compared with those of commercial FLUENT code, and show a good agreement.