Subsonic Flow Region on Blunted Cones in Supersonic Flow

Subsonic Flow Region on Blunted Cones in Supersonic Flow

This article investigates both experimentally and numerically the complicated flow around the blunted cone of semi-apex angle 20-45 degrees at Mach number 1.4-3.0. Especially, emphasized is the structure of subsonic flow region on the cone surface, that is caused by the transition from the over-expa...

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Veröffentlicht in:Aeronautical and Space Sciences Japan 1987/05/05, Vol.35(400), pp.253-259
Hauptverfasser: TANI, Takashi, ARAI, Norio, TAKEHANA, Koetsu, SEKINE, Hideo, HIROSE, Naoki
Format: Artikel
Sprache:jpn
Schlagworte:
Aerodynamics
Blunted Cone
Supersonic Flow
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Beschreibung
Zusammenfassung:This article investigates both experimentally and numerically the complicated flow around the blunted cone of semi-apex angle 20-45 degrees at Mach number 1.4-3.0. Especially, emphasized is the structure of subsonic flow region on the cone surface, that is caused by the transition from the over-expanded flow at the nose to the re-compression on the cone. Both results are in good agreement with each other. Consequently, it is shown that the numerical analysis of inviscid flow is very practical for such a complicated flow.
ISSN:0021-4663
2424-1369
DOI:10.2322/jjsass1969.35.253