Overview of Flow Diagnosis in a Shock Tunnel

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 aerother...

Full description

Saved in:
Bibliographic Details
Published inInternational journal of aeronautical and space sciences Vol. 18; no. 3; pp. 425 - 435
Main Authors Kim, Ikhyun, Lee, Sungmin, Park, Gisu, Lee, Jong Kook
Format Journal Article
LanguageEnglish
Published 한국항공우주학회 01.09.2017
Subjects
항공우주공학
Shock tunnel
Hypersonic
Aerothermodynamics
Online AccessGet full text
ISSN2093-274X
2093-2480
DOI10.5139/IJASS.2017.18.3.425

Cover

More Information
Summary: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. KCI Citation Count: 15
ISSN:2093-274X
2093-2480
DOI:10.5139/IJASS.2017.18.3.425