• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.5
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• pp.93-99
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• 2003

The determination of thrust is essential in design and evaluation of a hypersonic airbreathing propulsion device. Conventional methods to determine the thrust is using thrust stand or force measurement system. However, these conventional methos are not applicable to the case where thrusts stands are impractical, such as free jet testing of engines, and model combustor. For this reason, the thrust determination method from measured pitot pressure is considered and validated. Validation of thrust determination from pitot pressures can be achieved by comparing the actual thrust from thrust stand. For validation purpose, a small-scale supersonic wind tunnel is installed on the thrust stand. Thrusts are measured while pressures are measured simulaneously. Then, the thrust from pitot pressure measurements are compared with the measured thrust and theoretical thrusts.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2002.04a
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• pp.73-76
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• 2002

본 연구에서는 기존의 추력측정 방법보다 간단한 추력측정 방법으로서 피토 압력을 이용한 방법을 제안하였고, 이의 검증을 위해 소형 추력측정기를 제작하였다. 추력측정기를 이용하여 모델로켓 모터 및 초음속 풍동의 추력측정을 통하여 그 가능성을 확인하였고 본 연구의 목표인 피토압력과 추력측정기를 이용한 측정 추력의 비교연구가 계획되어 있다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.12
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• pp.18-24
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• 2006

Passive control of the shock wave/turbulent boundary-layer interaction utilizing slotted plates and a porous plate over a cavity has been carried out. Effect of various slot configurations on the characteristics of the interaction has been observed. Pitot/wall surface pressure distributions and flow visualizations including Schlieren images, kerosene-lampblack tracings and interference fringe patterns over a thin oil-film have been obtained at the downstream of the shock interactions. For the streamwise-slot configuration, a local higher pitot pressure was noticed at the downstream of the interaction as compared with the case of no control, however, not much improvement in pitot pressure was observed for the spanwise-slot configuration.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2001.11a
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• pp.75-76
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• 2001

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.11a
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• pp.327-330
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• 2006

Numerical study on the passive control of the oblique shock wave/turbulent boundary-layer interaction control utilizing slotted plates over a cavity has been carried out. Numerical results have been compared with the experimental observations, such as pitot/wall surface pressures and Schlieren flow visualizations, obtained for the same boundary conditions. It was found that the present numerical results shows a good agreement with experimental data. Further, the effect of different slot configurations including various number, location and angle of slots on the characteristics of the interactions are also tested, focusing on the variation of the piot pressure and the boundary-layer characteristics downstream of the interaction and the recirculating mass flux through cavity.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.4
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• pp.47-56
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• 2005

In GPS/INS/barometer navigation system for UAV, vertical channel damping loop was introduced to suppress divergence of the vertical axis error of INS, which could be reduced to the level of accuracy of pressure altitude measured by a pitot-static tube. Because static pressure measured by the pitot-static tube depends on the speed and attitude of the vehicle, static pressure error models, based on aerodynamic data from wind tunnel test, CFD analysis, and flight test, were applied to reduce the error of pressure altitude. Through flight tests and sensitivity analyses, the error model using the ratio of differential pressure and static pressure turned out to be superior to the model using only differential pressure, especially in case of high altitude flight. Both models were proposed to compensate the effect of vehicle speed change and used differential and static pressure which could be obtained directly from the output of pressure transducer.

• Journal of the KSME
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• v.23 no.5
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• pp.344-348
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• 1983

유속의 최초 측정방법은 Torricelli (1608-1647)가 Bernoulli 방정식을 오리피스에 적용하여 유속 계산식 v =k.root.2gh를 유도하였고, 그 이후 역시 Bernoulli 방정식을 이용하여 Henri Pitot (1695-1771)는 정체점에 대한 이론을 고려하여 정체압을 측정하는 방법으로 가는관을 이용하여 Seine 강의 유속을 측정하는데 성공하므로서 이론적인 유속계산식 v =k.root.2gh는 가장 원시적인 피토우관(Pito-tube) 이나 오리피스에 의한 유속계산식이지만, 현재에 아무리 전기적인 정밀측정 방법과 레이저에 의한 측정방법이 개발되어도 결국 피토우관에 의한 측정값이나 압력측정치와의 교정(Calibration)이 선행되지 않으면 안되기 때문에, 피토우관에 의한 측정방법은 가장 원시적 이면서 가장 정확한 측정방법의 하나이다. 다만 피토우관에 의한 측정은 속도장내의 평균속도를 측정하게 되고 난류성분의 해석이 불가능하며, 그 측정이 일차원 유동에 국한된다는 것이 단점 으로 되어 있다. 이러한 점들을 보완할 수 있는 측정장치 들이 많이 개발되고 있으나 본 해설 에서는 공기유동의 경우 우리가 가장 많이 사용하고 있는 열선풍속계에 대하여 그 용법을 논하기 로 한다.

• Proceedings of the KSME Conference
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• 2002.08a
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• pp.253-254
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• 2002

The determination of thrust is very important in hypersonic air-breathing propulsion design and evaluation. Because of the short flow-residence time in the combustor, the evaluation of engine performance is strongly influenced upon the engine thrust. Conventional methods to determine the thrust is using thrust stand or force measurement system. However, these methods cannot be applied to the case where thrust stands are impractical, such as free jet testing of engines, and model combustor. With this reason, the thrust determination method from measured pilot pressure is considered and evaluated.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.36 no.3
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• pp.233-240
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• 2012

An experimental study to improve the impingement characteristics of the assist gas in laser cutting was carried out. For various assist-gas pressures, and locations and installation angles of the nozzle, the characteristics of the impingement of the jet from a supersonic rectangular nozzle were compared to those previously observed for typical circular nozzles. Schlieren flow visualizations and Pitot pressure measurements downstream of the kerf surface were utilized for this purpose. The present rectangular supersonic nozzle decreased the strength of the Mach disc occurring at the corner of the kerf surface, and thus, could weaken the separation of the assist gas on the kerf surface and increase the Pitot pressures downstream compared to conventional circular nozzles.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.613-617
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• 2011

Korea Aerospace Research Institute has been designed and manufactured various thurst nozzles of the scramjet engine for optimized configuration. The test campaign for thurst nozzle characteristics was performed at T4 free-piston shock tunnel in University of Queensland, Australia. Total 8 kinds of thrust nozzles and 2 kinds of side walls were manufactured for this campaign. In this paper, the design and specification of thrust nozzles was reported. Based on the static pressure distribution of the engine and pitot pressure distributions at nozzle exit, The positive net thurst was observed with baseline case of the test campaign.