Overview of Flow Diagnosis in a Shock Tunnel

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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.
Publisher
KOREAN SOC AERONAUTICAL & SPACE SCIENCES
Issue Date
2017-09
Language
English
Article Type
Article
Keywords

PRESSURE MEASUREMENTS; COAXIAL THERMOCOUPLE; FACILITIES; STANDOFF; BODIES; AIR

Citation

INTERNATIONAL JOURNAL OF AERONAUTICAL AND SPACE SCIENCES, v.18, no.3, pp.425 - 435

ISSN
2093-274X
DOI
10.5139/IJASS.2017.18.3.425
URI
http://hdl.handle.net/10203/228634
Appears in Collection
AE-Journal Papers(저널논문)
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