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Generic lambda wing configuration with classical and novel control surfaces and highly integrated intakes

Rein, Martin (2018) Generic lambda wing configuration with classical and novel control surfaces and highly integrated intakes. In: Kolloquium über neuere Arbeiten auf dem Gebiete der Mechanik und Strömungslehre, TU Wien. Kolloquium über neuere Arbeiten auf dem Gebiete der Mechanik und Strömungslehre, 28. Juni 2018, Wien Österreich.

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Abstract

A study on the aerodynamics of a generic tailless lambda wing configuration at transonic Mach numbers is reported with an emphasis on both, stability and control and the effect of an intake on the lee side of the vehicle. The SACCON (Stability And Control CONfiguration) represents a generic unmanned combat air vehicle configuration that has also been the subject of a task group of NATO’s Science and Technology Organization (STO). The effect of classical and novel control concepts has been tested in the transonic wind tunnel of the German–Dutch Wind Tunnels to determine their effects on the lateral directional and longitudinal stability of the aircraft. In addition, the influence of a highly integrated flow-through intake on the vortical flow about the generic configuration has been examined by considering two versions of the model: a clean one without intake, and a modified one with intake and exhaust openings on the lee side. 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. The study has been complemented by an investigation of the combined effects of boundary layer ingestion and an S-duct diffuser on flow conditions at the engine face. The main focus of the investigations is on the impact of boundary layers on intake performance and on limitations of diverterless intakes due to boundary layer ingestion. To this end, the dependence on flow parameters of total pressure distortions in a generic intake has been examined in a parametric study in a blowdown wind tunnel. In order to form a boundary layer of well-defined thickness ahead of the intake the model was arranged on a flat plate.

Item URL in elib:https://elib.dlr.de/122666/
Document Type:Conference or Workshop Item (Speech)
Title:Generic lambda wing configuration with classical and novel control surfaces and highly integrated intakes
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Rein, MartinASUNSPECIFIED
Date:28 June 2018
Journal or Publication Title:Kolloquium über neuere Arbeiten auf dem Gebiete der Mechanik und Strömungslehre, TU Wien
Refereed publication:No
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Status:Published
Keywords:Aerodynamics, Transonics, delta wing, vortex, intake, s-duct, diffuser, boundary layer ingestion
Event Title:Kolloquium über neuere Arbeiten auf dem Gebiete der Mechanik und Strömungslehre
Event Location:Wien Österreich
Event Type:Other
Event Dates:28. Juni 2018
Organizer:Institut für Strömungsmechanik und Wärmeübertragung, Technische Universität Wien
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 for Aerodynamics and Flow Technology > High Speed Configurations, GO
Deposited By: Rein, Prof.Dr. Martin
Deposited On:02 Nov 2018 14:05
Last Modified:07 Jan 2019 02:46

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