• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.388-391
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• 2012

Intake start characteristics of a Mach 5 scramjet engine were investigated experimentally. Intake unstart was observed. The model-facility interaction or excessive internal contraction ratio were attributed to this unstart. Intake start was achieved by changing the model position to remove the model-facility interaction, and by modifying the cowl to give smaller contraction ratio.

• Journal of the Korean Society of Propulsion Engineers
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• v.9 no.3
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• pp.38-48
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• 2005

For the development of Scramjet engine technology, intake designing processes are investigated. The basic geometry is determined by the inviuld relation such as shock wave relations and geometric relations. Furthermore, bleed duct is installed for preventing boundary layer development and shock wave impingement. Performance of the designed intake is validated by numerical analysis. As a result, double- wedge intake showed better characteristics in total pressure recovery than single-wedge intake.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.47 no.3
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• pp.195-203
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• 2019

Since the hypersonic intake is directly related to the overall performance of the engine, it is essential to analyze performance characteristics under various off-design conditions. In this paper, Busemann intake and conical intake with external compression were designed, and numerical simulations were performed at on/off-design conditions. Based on the results, the overall performance characteristics of two types of intake were analyzed in various Mach numbers and angle of attacks. The results showed that performance degradation of Busemann intake with truncation angle of 2 degrees was minimal. Also, the performance of Busemann intake was higher than external compression intake at various Mach numbers, however, the starting characteristics were significantly reduced with an angle of attack.

• 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.

• Journal of the Korean Society of Propulsion Engineers
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• v.26 no.1
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• pp.77-87
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• 2022

In order to perform the scramejt engine intake ground test using the Scramjet Engine Test Facility(SETF) of the Korea Aerospace Research Institute. we introduced the test availability check procedure that is generally conducted. The design process of the newly manufactured Mach 5 nozzle for the scramjet intake test was summarized, a device for checking the core flow distribution of the nozzle was explained, and the core flow test analysis results were written. Through a series of test results, it was confirmed that the intake was located in the new Mach 5 nozzle core.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.992-995
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• 2011

A study on the performance design schemes of the supersonic air intakes applied to the supersonic air-breathing propulsion system(Ramjet/Scramjet) was conducted and for two kinds of air intakes, the preliminary configuration designs and the performance analysis models were established. For axisymmetric conical air intake and two dimensional rectangular air intake, the performance effects were assessed according to compression angles and shock wave numbers.

• Journal of the Korean Society of Propulsion Engineers
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• v.22 no.5
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• pp.49-58
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• 2018

This paper introduces a research on the control method design for the subsonic intake flow of a dual-combustion ramjet engine. To design the control method, the intake flow dynamic response characteristics, based on a designated flow condition and intake geometry, are investigated, and a control method concept considering the intake flow characteristics is established. Using a dynamic simulation model of a dual-combustion ramjet, control input/output linearized models are obtained such that a control loop design based on linearized models can be accomplished. Finally, from various control loop simulations, the performance of the control method, including its control loop stability, is evaluated.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.331-334
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• 2011

The performance of ramjet engine is closely associated with a supersonic intake. In this study, experiments and computational simulations were conducted to observe the internal flow characteristics of the supersonic intake. The supersonic intake which have self-starting characteristics was designed and manufactured. The flow characteristics was analyzed from the experimental results using the supersonic wind tunnel testing and computational results using RANS equation and Menter's SST turbulence model. The detailed visualization results were suggested for the pseudo-shock wave of stable operations and for the inlet buzz phenomenon of unstable operations.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.335-338
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• 2007

This study carried out the 2D modeling for estimating the intake loss that is a important installed loss for the precise installed performance analysis of a gas turbine engine, and the 0D performance map that represents intake pressure loss change depending on flight Mach number and air mass flow rate was generated using the 2D modeling results. In order to evaluate the generation procedure of the intake performance map, the intake map generation was applied to a commercial aircraft intake configuration.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.11a
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• pp.339-343
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• 2006

Model SCRamjet Engine intake is designed for Ground test. The designed Intake provides hot and slow flow with the combustor. Flow separation is controlled by the shock wave segregation based on the Korekegi criteria. With Kantrowitz limit analysis, side wall cut out region is also set for the self start.