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논문 기본 정보

자료유형
학술저널
저자정보
Ikhyun Kim (Korea Advanced Institute of Science and Technology) Sungmin Lee (Korea Advanced Institute of Science and Technology) Gisu Park (Korea Advanced Institute of Science and Technology) Jong Kook Lee (Agency for Defense Development)
저널정보
한국항공우주학회 International Journal of Aeronautical and Space Sciences International Journal of Aeronautical and Space Sciences Volume.18 Number.3
발행연도
2017.9
수록면
425 - 435 (11page)
DOI
10.5139/IJASS.2017.18.3.425

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초록· 키워드

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In this work, an overview of flow diagnosis in a shock tunnel is made by means of using established techniques that are easy to setup, economical to arrange, and simple to measure. One flow condition was considered having Mach number of 6 at the nozzle-exit, regarded as freestream. Measured aerothermodynamic data such as shock wave speed, wall static and total pressures, surface heat flux, and shock stand-off distance ahead of test model showed good agreement with calculation. This study shows an overall procedure of flow diagnosis in a shock tunnel in a single manuscript. Outcomes are thought to be useful in the field of education and also in a preliminary stage of high-speed vehicle design and tests, that need to be performed within a short time with decent accuracy.

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Abstract
1. Introduction
2. Overview of flow diagnosis
3. Conclusions
References

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