A new visualizing method of streamlines around hypersonic bodies.
نویسندگان
چکیده
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Approximate Viscous Shock-Layer Analysis of Axisymmetric Bodies in Perfect Gas Hypersonic Flow
In this paper, an approximate axisymmetric method is developed which can reliably calculate fully viscous hypersonic flow over blunt-nosed bodies. In this method, a Maslen’s second-order pressure expression is used instead of the normal momentum equation. The combination of Maslen’s second-order pressure expression and viscous shock layer equations is developed to accurately and efficiently com...
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This study concerns the hypersonic flow over blunt bodies in two specific cases. The first is the case when the Mach number is infinite and the ratio of the specific heats approaches one. This is sometimes referred to as the ‘Newtonian limit’. The second is the case of infinite Mach number and very large streamwise distance from the blunt nose with a strong shock wave, or the ‘blast wave limit ...
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ژورنال
عنوان ژورنال: JOURNAL OF THE FLOW VISUALIZATION SOCIETY OF JAPAN
سال: 1989
ISSN: 1884-0361,0287-3605
DOI: 10.3154/jvs1981.9.349