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An Experimental Study of Chin-Intakes for Airbreathing Missiles with High Agility

Herrmann, Dirk and Triesch, Klaus and Gülhan, Ali (2007) An Experimental Study of Chin-Intakes for Airbreathing Missiles with High Agility. Journal of Propulsion and Power, 24 (2), pp. 236-244. AIAA.

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Abstract

The performance of three chin-intakes for airbreathing missiles with high agility has been investigated in a large maneuver range at supersonic speed. This experimental study is recovery and mass flow were discovered at angles of attack greater than 18°. To understand these effects in more details chin-intakes have been analyzed at a design Mach number of 3.0 at angles of attack ranging from -30° to 30° and at angles of sideslip ranging from -30° and 30° in the Trisonic Wind Tunnel. The results clearly show that boundary layer flow, vortices and flow sepration are responsible for the losses of pressure recovery and mass flow. The subsequently added boundary layer bleed permits a better pressure recovery and a delay of the intake buzzing.

Document Type:Article
Title:An Experimental Study of Chin-Intakes for Airbreathing Missiles with High Agility
Authors:
AuthorsInstitution or Email of Authors
Herrmann, DirkUNSPECIFIED
Triesch, KlausUNSPECIFIED
Gülhan, AliUNSPECIFIED
Date:2007
Journal or Publication Title:Journal of Propulsion and Power
Refereed publication:Yes
In ISI Web of Science:Yes
Volume:24
Page Range:pp. 236-244
Publisher:AIAA
Series Name:Journal of Propulsion and Power
Status:Published
Keywords:missiles, air breathing propulsion, high agility, ramjet performance
HGF - Research field:Aeronautics, Space and Transport (old)
HGF - Program:Aeronautics
HGF - Program Themes:Rotorcraft
DLR - Research area:Aeronautics
DLR - Program:L AR - Aircraft Research
DLR - Research theme (Project):L -- no assignement
Location: Köln-Porz
Institutes and Institutions:Institute of Aerodynamics and Flow Technology
Deposited By: Christine Adams
Deposited On:26 Mar 2008
Last Modified:15 Jan 2010 02:06

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