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Experimental investigation of isolated inlets for high agile missiles

Herrmann, Dirk and Triesch, Klaus (2006) Experimental investigation of isolated inlets for high agile missiles. Aerospace Science and Technology, 10, pp. 659-667.

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Abstract

Experimental studies are accomplished with two axially symmetric inlet models with different internal compressions. Main interest lies in covering a large and flexible maneuver range at supersonic speed. This requires an analysis of the performance such as pressure recovery and mass flow. The inlets are analyzed at the design Mach number MA = 3 in an angle of attack range of 0° ≤ α ≤ 30° in the Vertical Wind Tunnel (VMK) in Cologne. The tests indicate an operability up to α = 30°. Furthermore a loss of pressure recovery and mass flow is discovered at an angle of attack of α ≥ 18°. Accordingly boundary layer bleed is implemented to get a better pressure recovery and a delayed buzzing.

Item URL in elib:https://elib.dlr.de/47791/
Document Type:Article
Title:Experimental investigation of isolated inlets for high agile missiles
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Herrmann, DirkUNSPECIFIEDUNSPECIFIED
Triesch, KlausUNSPECIFIEDUNSPECIFIED
Date:2006
Journal or Publication Title:Aerospace Science and Technology
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Volume:10
Page Range:pp. 659-667
Editors:
EditorsEmail
Elsevier, UNSPECIFIED
Status:Published
Keywords:Axially symmetric inlet, Ramjet, boundary layer bleed, supersonic flow
HGF - Research field:Aeronautics, Space and Transport (old)
HGF - Program:Aeronautics
HGF - Program Themes:Aircraft Research (old)
DLR - Research area:Aeronautics
DLR - Program:L AR - Aircraft Research
DLR - Research theme (Project):L - Military Technologies (old)
Location: Köln-Porz
Institutes and Institutions:Institute of Aerodynamics and Flow Technology
Deposited By:INVALID USER
Deposited On:28 Mar 2007
Last Modified:15 Jan 2010 00:27

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