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
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Sprache:jpn
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Aerodynamics
Blunted Cone
Supersonic Flow
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container_end_page 259
container_issue 400
container_start_page 253
container_title Aeronautical and Space Sciences Japan
container_volume 35
creator TANI, Takashi
ARAI, Norio
TAKEHANA, Koetsu
SEKINE, Hideo
HIROSE, Naoki
description 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.
doi_str_mv 10.2322/jjsass1969.35.253
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source EZB-FREE-00999 freely available EZB journals
subjects Aerodynamics
Blunted Cone
Supersonic Flow
title Subsonic Flow Region on Blunted Cones in Supersonic Flow
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