• Journal of the Korean Society for Precision Engineering
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• v.10 no.1
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• pp.28-33
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• 1993

Measurements errors due to sound velocity effect on vibrating gas densimeters were described. Nitrogen was used to calibrate the densimeter, and oxygen was employed to determine a coefficient for the compensation of sound velocity effect. Sound velocity effects were shown with methane at temperatures of 7.97, 19.93 and 39.57 .deg. C, and pressures up to 3.6 Mpa. A relative error of about 1% was introduced when the nitrogen calibrated densimeter was used to measure densities of pure methane. A method of sound velocity effect compensation was able to reduce the error down to 0.1%.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.12
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• pp.1028-1036
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• 2014

A design procedure is established for hypersonic nozzles by using MOC(Method of Characteristics) and CFD. The inviscid nozzle contour is designed by MOC, then BLC(Boundary Layer Correction) is made by evaluating the boundary layer thickness from viscous CFD analysis. By comparing various definitions of the boundary layer thicknesses, it seems that the boundary layer thickness of 95% speed of the maximum value at the cross section satisfies best the design Mach number. Design procedure is as follow; MOC design, grid generation, inviscid analysis, viscous analysis, BLC and viscous analysis for confirmation and post-processing. All procedures are made automatically by using the batch processing.

• Journal of the Korean Society of Propulsion Engineers
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• v.18 no.6
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• pp.1-10
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• 2014

The optimal method to intuitively and systematical design hypersonic intakes is reported. In Mach 7 flow condition, the hypersonic intake model designed by theoretical approach is corrected by CFD(Computational Fluid Dynamics) analysis based on viscous flow condition, leading to the optimum hypersonic intake model. For performance comparison with CFD analysis, the double ramp intake is superior to the single ramp intake. Furthermore, in the off-design condition, the performance of the designed hypersonic intake is little degraded.

• 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.

• 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.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.50 no.5
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• pp.297-308
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• 2022

Most air-breathing aircraft operated in the hypersonic region are equipped with a scramjet engine. In a scramjet engine, a shock wave generated at an inlet acts as a compressor for a general gas turbine engine instead, so total pressure loss caused by the shock wave is considered very important. In this study, to minimize total pressure loss, a method of designing an external compression inlet using isentropic compression surface was proposed, and an external compression inlet with 3-deflection angles and Busemann inlet were designed under the same conditions. After that, through computational analysis, the performance characteristics at off-design conditions were compared. Each inlet shape was truncated according to the length of the 3-ramp external compression inlet, and the boundary layer correction was performed. The isentropic external compression inlet showed superior performance at the design point, but under the off-design conditions, its performance was degraded compared to the 3-ramp external compression inlet.

• Journal of the Korean Institute of Telematics and Electronics
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• v.26 no.7
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• pp.98-105
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• 1989

To characterize the biological tissue, the new method to measure the ultrasonic velocity is presented in this paper. The influence of the dispersion effect on the estimation of the ultrasonic velocity is mostly neglected. A more efficient method determining the minimum phase spectrum is developed to characterize the frequency dispersion form the spectral magnitude function. To eliminate the frequency dispersion, the signal-decomposition method is also proposed. Computer simulations are performed to verify the algorithms.

• 한국지구물리탐사학회:학술대회논문집
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• 2009.10a
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• pp.167-173
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• 2009

Bathymetry survey around the Baengnyeong-do was made by the Korea Hydrographic and Oceanographic Administration (KHOA), using the Simrad EM3000 Multi-Beam EchoSounder (MBES) mounted at the hull of the R/V Badaro 1. Sound velocity were monitored with frequent sound velocity profiler(SVP) casts during the acoustic measurements. The depth distribution and fluctuation of thermocline varied locally owing to the effect of several current flows such as Kuroshio current and Yellow sea coastal waters. These uncertainties cause the falling-off in accuracy of MBES results. In this paper, the bathymetry results will be presented and their accuracy will be discussed along with comparisons to the time and spatial variations in sound velocity profile.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.2
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• pp.130-135
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• 2007

Wind tunnel test for Smart UAV power model has been conducted at KARI LSWT for about 3 months. The static model is used for the base plane and the power effect of tilt rotor is simulated by the tilt-rotor test rig installed in the test section. Although the genuine power effect is the difference between power-on and off tests. The existence of struts for power effect test produced unwanted form of interference and caused the change in flow angularity. To precisely evaluate power effect, a special approach is applied to Smart UAV test.

• Aerospace Engineering and Technology
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• v.5 no.2
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• pp.47-52
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• 2006

The external balance of KARl LSWT is installed by Aerotech at 1998. It has been used for more than 70 tests until 2004. The upgrade and re-calibration program are planed to solve the problem that revealed in 7-years operation and to increase the accuracy of the system. In this paper, 3 calibration results are presented. The first one is the results done by Aerotech at 1998, the second one is the results by using quick-loading system at 2004, and the last one is the results done at 2005.