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Generic Lambda Wing Configuration in Compressible Flow: Effect of Highly Integrated Intakes

Rein, Martin and Gardner, Anthony Donald (2015) Generic Lambda Wing Configuration in Compressible Flow: Effect of Highly Integrated Intakes. Journal of Aircraft, 52 (3), pp. 972-980. American Institute of Aeronautics and Astronautics (AIAA). DOI: 10.2514/1.C033177 ISSN 0021-8669

Full text not available from this repository.

Official URL: http://arc.aiaa.org/doi/pdf/10.2514/1.C033177

Abstract

The influence of a highly integrated flow-through intake on the vortical flow about a generic lambda wing configuration is studied for 0.55 · 106 < Re < 2.45 · 106 and 0.3 < M < 0.75. To this end, two versions of the configuration are considered: a clean one without intake, and a modified one with intake and exhaust openings on the lee side. Experimental investigations were performed in the transonic wind tunnel Göttingen of the German–Dutch Wind Tunnels. Forces and moments were measured by a strain gauge balance, and the pressure distribution on the lee side of the model was determined by pressure-sensitive paint. An estimate of the nondimensional mass flux through the intake is obtained from direct pressure measurements within the ducts. The experimental tests are supplemented by numerical investigations performed for two Mach numbers. The effect of the intake is discussed by comparing results obtained for the two versions of the model under otherwise same conditions.

Item URL in elib:https://elib.dlr.de/96352/
Document Type:Article
Title:Generic Lambda Wing Configuration in Compressible Flow: Effect of Highly Integrated Intakes
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Rein, Martinmartin.rein (at) dlr.deUNSPECIFIED
Gardner, Anthony Donaldtony.gardner (at) dlr.deUNSPECIFIED
Date:2015
Journal or Publication Title:Journal of Aircraft
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:Yes
In ISI Web of Science:Yes
Volume:52
DOI :10.2514/1.C033177
Page Range:pp. 972-980
Publisher:American Institute of Aeronautics and Astronautics (AIAA)
ISSN:0021-8669
Status:Published
Keywords:delta wings, vortical flows, integrated intakes, wind tunnel tests
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:fixed-wing aircraft
DLR - Research area:Aeronautics
DLR - Program:L AR - Aircraft Research
DLR - Research theme (Project):L - Military Technologies
Location: Göttingen
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > High Speed Configurations
Institute of Aerodynamics and Flow Technology > Helicopters
Deposited By: Micknaus, Ilka
Deposited On:16 Jun 2015 10:52
Last Modified:08 Mar 2018 18:41

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